DoD 2019.2 SBIR Solicitation

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: The key objective of this work is to evaluate the mechanical properties and microstructural characteristics of post-process heat treatments of Additively Manufactured (AM) Ti-6Al-4V alloy including process-structure-property relationships. Tensile testing, smooth bar high cycle fatigue testing and microstructural analyses are to be performed on Laser Powder Bed Fusion (L-PBF) manufactured near net shape Ti-6Al-4V specimens having four heat treatment types after Hot Isostatic Pressing (HIP). These heat treatments are Mill-Anneal (MA), ANNeal (ANN), Solution Treat and Age (STA) and Beta Solution Treat and Overaged (BSOA). The resulting mechanical properties and microstructures will be compared to the traditional Ti-6Al-4V alloys bars, forgings and castings. The quantitative process-structure-property relationships will be determined with computational modeling with respect to build orientation. 

DESCRIPTION: Additive Manufacturing (AM) is a new production technology that enables reduced manufacturing steps, part consolidation and production of near net shape parts from 3-D model data. Current applications mainly focus on secondary structures or other non-critical applications. Recent developments in AM technology and AM Standards offer great potential to implement AM produced part in the US Army. In the past few decades, there is an increasing interest to produce metallic AM parts for structural and non-structural applications, as these materials show acceptable performances compared to the traditional materials with shorter lead times, less material usage and near net-shape parts [1-8]. The use of AM titanium alloy replacement of a currently used traditional titanium alloy in the US Army helicopters with a same traditional alloy heat treatment types may not provide an increased utilization of the AM titanium alloy and may cause additional performance risk since heat treatment for AM titanium alloy is not optimized. The current standard ASTM F2924 [9] of the AM Ti-6Al-4V alloy mechanical properties in all direction requires minimum tensile properties (130 ksi UTS/120 ksi YS/10% Elong) regardless of heat treatment types and part thicknesses. The thickness of the part affects the grain size of the part during solidification as such the grain sizes are smaller for the small thickness compared to the thick part. Therefore, tensile properties are higher for a part with small grains even though both part had same heat treatment types. On the other hand, the tensile properties are also depends on heat treatment types. For example, annealing heat treatment provides lower tensile properties compared to the solution heat and aged heat treatment. Therefore, the effects of heat treatment types coupled with part thickness and resulting mechanical properties need to be thoroughly investigated. In this study, the L-PBF AM process will be used to manufacture near net shape AM Ti-6Al-4V test specimens, and evaluate the effect of post-processing heat treatment types on tensile and fatigue properties, compared to the baseline Ti-6Al-4V alloy bar, forging and casting material properties. To understand the process-structure-property relationships, computational modeling is to be utilized to predict the quantitative mechanical properties such as tensile, yield, elongation and fatigue strength. The project will be conducted in three phases. Phase I will focus on assessment, design and selection of parameters, computational model, manufacturing options and procurement of AM Ti-6Al-4V alloy powder. Phase II will focus on demonstrating the ability to manufacture near net-shape of tensile and fatigue specimens, perform tensile, fatigue tests and evaluate tensile, fatigue test results of four heat treatment types (MA, ANN, STA and BSTOA) and quantitative prediction of process-structure-property relationships along different directions. Ten tests (10) at room temperature per heat treatment types will be evaluated for both tensile and high cycle fatigue (0.1 R-ratio) tests. Beta transus temperature of the two specimens will be determined for heat treating guidance. The chemical composition and density of the each lot will be determined. The chemical composition and physical properties of the Ti-6Al-4V powder will be verified. Only one batch of virgin powder and no recycled powder will be used. A few trial manufacturing is to be made to verify specimen sizes, quality and tensile properties. Phase III will focus introduction of AM Ti-6Al-4V alloy into a broad range of defense and civilian applications. This technology has been demonstrated in a laboratory research scale and prototype parts. The current effort would use existing technology to develop an optimized heat treatment types for AM Ti-6Al-4V alloy process utilizing simple shaped tensile and fatigue specimens. It is noted that the listed references [9-20] are to be used for general guidance on materials, manufacturing, heat treatment, testing and reporting to accomplish the objective of this project. The project’s three major phases are described below. 

PHASE I: Phase One evaluates the engineering merit and feasibility of the proposed technology. It identifies and builds team with industrial partners, design and select AM Ti-6Al-4V powder type, size and amount of experimental test specimens, AM manufacturing and, assesses application and manufacturing options, addresses producibility and inspectibility using these test specimens, selects predictive computer modeling and investigates the overall benefits of the project. The interrelations among AM processed Ti-6Al-4V alloy heat treating conditions and resulting microstructure parameters (alpha layer thickness, alpha and beta phase content, grain size, density, etc.) and mechanical properties are still not fully understood. To understand the process-structure-property relationships computational modeling need to be utilized to predict the quantitative mechanical properties. The objective of the process-structure-property relationships between the heat treating conditions and microstructural features is to be able to predict the microstructure and resulting mechanical properties for a given part geometry, size, and feature orientations for a given heat treating conditions. Such a model would be the basis for improving first part yield and enabling rapid part qualification. In order to verify the process-structure-property relationships, experimentally measured microstructural features and tensile properties are required in x, y and z directions. A generic computational model or a modified one to predict properties could be used for predicting process-structure-property relationships. To predict a complex part process-structure-property relationships, selected complex shaped parts will be modeled to determine properties. These representative complex shaped parts will be manufactured in Phase II and mechanical properties and microstuctural features will be measured with respect specimen orientations for modeling verification. Recommended computational modeling is to be demonstrated with open source microstructure and mechanical data for the AM Ti-6Al-4V alloy. Further ideas beyond described are welcome. An appropriate process modeling could be used to minimize process defects and maximize the mechanical properties for optimum producibility if needed and funding are available. Required Phase I deliverables include monthly progress reports, final technical report including specimen sizes, testing specimens locations, tests, powder specification and amount, AM build layout and manufacturing plans, predicted computational model examples demonstrating the process-structure-property relationships including complex shapes. 

PHASE II: Phase Two will manufacture the specimens and evaluate tensile and fatigue test results, predictive computational modeling compared to the traditional Ti-6Al-4V alloy bars, forgings and castings. The process will utilize an L-PBF process. The shapes of AM specimens will be simple-shaped L-PBF manufacturing. The overall dimension in length could be 8.0 inches with three wall thickness ranges as 0.25, 0.50, 1.00 and 2.00 inches with appropriate machining stocks. Any required radiuses could be 0.02 inches. All specimens will undergo HIP prior to the following heat treatments: 1) mill-anneal, 2) anneal, 3) solution treated and age and finally 4) beta solution treated and overaged. Tensile, fatigue, hardness, density, optical microscopy, scanning electron microscopy and computer tomography (CT) analyses are to be utilized to generate and analyze the resulting data during the Phase II effort. Ten (10) tests will be performed at room temperature per heat treatment types. Additionally, ten (10) tests will be performed at room temperature as AM manufactured and as HIPed for baseline comparison. Tensile, fatigue, hardness, density, optical microscopy, scanning electron microscopy and computer tomography (CT) analyses are to be utilized to generate and analyze the resulting data during the Phase II tensile evaluation. The specimens will undergo both tensile and high cycle fatigue (0.1 R-ratio) tests. Beta transus temperature of the two specimens as well as the chemical composition of each lot will be determined for heat treating guidance. Additionally, the chemical composition and physical properties of the Ti-6Al-4V powder will also be verified. Only one batch of virgin powder (no recycled powder) will be used, and all specimens will come from the same AM build feedstock. Trial printed specimens will be made to verify specimen sizes, quality and tensile properties. The interrelations among AM processed Ti-6Al-4V alloy heat treating conditions and resulting microstructure parameters (alpha layer thickness, alpha and beta phase content, grain size, density, etc.) and mechanical properties are to be determined. To understand the process-structure-property relationships, computational modeling is to be utilized to predict the quantitative mechanical properties. Such a model would be the basis for improving first part yield and enabling rapid part qualification. In order to verify the model, experimentally measured microstructural features and tensile properties are required in x, y and z directions. The resulting data is to be used to validate the computational modeling. Required Phase II deliverables include bi-monthly progress reports, test reports, computational predictive mechanical property evaluation and a final technical report including powder chemical and physical properties, AM Ti-6Al-4V chemical analysis, CT and dimensional inspections, tensile, hardness, fatigue testing, microstructure, fractography analysis, computational model inputs to predict properties, verification and example of the model predictions. 

PHASE III: Phase Three will address the transition path of this technology resulting from Phase II effort to various US Army components with industrial partners and Original Equipment Manufacturers (OEMs). This technology has been demonstrated in a laboratory research scale and on prototype parts. This program effort would use existing technology to develop an optimized heat treatment process for AM Ti-6Al-4V alloys, quantitative process-structure-property relationships utilizing simple shaped tensile and fatigue specimens. It is noted that the listed references [9-20] are to be used for general guidance on materials, manufacturing, and heat treatment, testing and reporting to accomplish the objective of this project. The implementation targets are defense applications. The expected benefit of the resulting project data could become a heat treatment guide for AM Ti-6Al-4V alloy components used in US Army applications requiring tensile strength, fatigue strength and combination of both tensile and fatigue strength for performance requirements. The relevant technical data generated and experience gained in this project are expected to positively impact application of additively manufactured titanium components in a broad range of defense applications where light weight and reduced lead time are needed for very complex parts that use titanium components. All these project benefits will results in improved U. S. readiness and capability. 

REFERENCES: 

1: Seifi, M.

2:  Salem, A.

3:  Beuth, J.

4:  Harrysson, O.

5:  Lewandowski, J.J. Overview of Materials Qualification Needs for Metal Additive Manufacturing. JOM, 2016, 68, 747–764.

6:  Song, B.

7:  Dong, S.

8:  Zhang, B.

9:  Liao, H.

10:  Coddet, C. Effects of processing parameters on microstructure and mechanical property of selective laser melted Ti6Al4V. Mater. Des. 2012, 35, 120–125.

11:  Kranz, J. Herzog, D. and Emmelmann, C., Design Guidelines for Laser Additive Manufacturing of Lightweight Structures in Ti6Al4V, Journal of Laser Applications, 2015,Vol. 27, S1400-1-S14001-16.

12:  Vilaro, T.

13:  Colin, C.

14:  Bartout, J.D. As-Fabricated and Heat-Treated Microstructures of the Ti-6Al-4V Alloy Processed by Selective Laser Melting. Metall. Mater. Trans. A, 2011, 42, 3190–3199.

15:  Kong, C.J.

16:  Tuck, C.J.

17:  Ashcroft, A.I.

18:  Wildman, R.D.

19:  Hague, R. High density Ti-6Al-4V via SLM processing: Microstructure and mechanical properties. In Proceeding of the 22nd Annual International Solid Freeform Fabrication Symposium, Austin, TX, USA, 8–10 August 2011, 475–483.

20:  Quintana, O. A. Alvarez, J. McMillan, W. R. and Tomonto, C., Effects of Reusing Ti-6Al-4V Powder in a Selective Laser Melting Additive System Operated in an Industrial Setting, JOM, 2018,Vol.70, No. 9 1863-1869.

21:  Leuders, S.

22:  Thöne, M.

23:  Riemer, A.

24:  Niendorf, T.

25:  Tröster, T.

26:  Richard, H.A.

27:  Maier, H.J. On the mechanical behaviour of titanium alloy TiAl6V4 manufactured by selective laser melting: Fatigue resistance and crack growth performance. Int. J. Fatigue, 2013, 48, 300–307.

28:  Cao, F., Zhang, T., Ryder, M. A., and Lados, D. A., A Review of the Fatigue Properties of Additively Manufactured Ti-6AL-4V, JOM, 2018, Vol. 70, No. 3, 349-357.

29:  ASTM F2924-14, "Standard Specification for Additive Manufacturing Titanium-6 Aluminum-4 Vanadium with Powder Bed Fusion," ASTM International, West Conshohocken, PA, 19428.

30:  AMS2801B, "Heat Treatment of Titanium and Titanium Alloy," Issued 2003-03, Society of Automotive Engineers, Warrendale, PA 15096.

31:  ASTM F3049-14, "StandardGuide for Characterization Properties of Metal Powders for Additive Manufacturing Processes," ASTM International, West Conshohocken, PA, 19428.

32:  AMS7003, "Laser Powder Bed Fusion Process," Issued 2018-06, Society of Automotive Engineers, Warrendale, PA 15096.

33:  AMS7002, "Process Requirements for Production of Metal Powder Feedstock for Use in Additive Manufacturing of Aerospace Parts," Issued 2018-06, Society of Automotive Engineers, Warrendale, PA 15096.

34:  ASTM F3301-18, "Standard for Additive Manufacturing – Post Processing Methods –Standard Specification for Thermal Post-Processing Metal Parts Made Via Powder Bed Fusion," ASTM International, West Conshohocken, PA, 19428.

35:  ASTM F3122, "Standard Guide for Evaluation Mechanical Properties of Metal Materials Made via Additive Manufacturing Processes," ASTM International, West Conshohocken, PA, 19428.

36:  ASTM F2971, "Standard Practice for Reporting Data for Test Specimens Prepared by Additive Manufacturing," ASTM International, West Conshohocken, PA, 19428.

37:  ASTM B311, "Standard Test Method for Density of Powder Metallurgy (PM) Materials Containing Less Than Two Percent Porosity," ASTM International, West Conshohocken, PA, 19428.

38:  ASTM E1441, "Standard Guide for Computed Tomography (CT) Imaging," ASTM International, West Conshohocken, PA, 19428.

39:  ASTM F3303, "Additive Manufacturing – Process Characteristics and Performance: Practice for Metal Powder Bed Fusion Process to Meet Critical Applications," ASTM International, West Conshohocken, PA, 19428.

40:  AS1814, "Terminology for Titanium Microstructures." Society of Automotive Engineers, Warrendale, PA 15096.

KEYWORDS: Additive Manufacturing, Heat Treatment, Ti-6Al-4V Alloy, Tensile Properties, Microstructure, Laser, Powder Bed Fusion, Process Structure Property Relationships 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Cybersecurity systems need to take advantage of high assurance provided by state machines used for aviation and safety critical systems. Offeror shall research a high assurance state machine trusted computing base for a high assurance operating system. 

DESCRIPTION: Safety critical systems use state machines to achieve high computer security assurance levels. State machines make security reviews for EAL6 or higher tractable. Current generation aviation systems were not developed with strong computer security requirements. Past cyber threats, [1]-[2], current cyber treats, Spectre [3] and Meltdown [4], and future cyber treats need to be countered. Embedded system designs are typically based on commodity hardware optimized exclusively for speed – leading to critical cyber vulnerabilities that can have devastating effects on safety and mission effectiveness. This has also led to the unsustainable “Perimeter, Patch, Pray” Information Assurance strategy [5] that is simply impractical for fielded aviation and missile systems. We are interested in researching a separation kernel-like operating system consisting of a hardware state machine as the trusted computing base and a high assurance operating system. In terms of computer virtualization concepts: the trusted computing base is a hardware state machine and the OS can be compared to a guest operating system. Recent developments in the open source hardware and software communities have created the open source RISC-V [6] and OpenPiton [7] microprocessors and high assurance open source operating system, seL4 [8]. Open source architectures provide for more thorough security reviews compared to closed source systems [9]. Open source architectures also provide for lower life cycle system cost. We are interested in leveraging the open source communities for this research topic area. Preference will be given for open source hardware and operating system modules. 

PHASE I: For the Phase I proposal, offeror shall describe the feasibility of using a hardware and software co-design to create a high assurance state machine as the trusted computing base for a high assurance operating system. (1) Propose high assurance state machine trusted computing base concept. (2) Propose an operating system to take advantage of trusted computing base. (3) Propose a system architecture describing: hardware, microprocessor, state machine, operating system, and application software. (4) Describe the cybersecurity advantages of (3) over current commodity microprocessors and operating systems. (5) A plan to achieve a cybersecurity security rating of at least EAL6. (6) Describe potential Army, medical, and commercial applications; and (7) Provide a business model to market the proposed system. For the phase I effort, the offeror shall demonstrate the feasibility and security benefits of creating a high assurance hardware state machine trusted computing base and high assurance OS. (1) Develop models, simulations, prototypes, etc. to determine technical feasibility of developing a high assurance system (2) Deliver a System Architecture and Description Report; and (3) Deliver an EAL Certification Plan Report. 

PHASE II: Offeror shall develop a high assurance computer system based on offeror’s proposal and phase I effort. It is highly recommended that the offeror team with a government prime contractor. The offeror shall demonstrate high assurance computer system running an Army application (like Joint Multi-Role Technology Demonstrator [19]). The Offer shall propose potential applications for a system demonstration and implement an application with government concurrence. Offeror shall deliver a year 1 report and a year 2 report describing artifacts, documents, verification tests, etc. completed following the plan in the Phase I document EAL Certification Plan Report. Offeror shall deliver 2 prototype systems to the government point of contact for test and evaluation with all software tools and licenses (if required) to build and use the system. Offeror shall provide 2 days of on-site training for the system. 

PHASE III: Offeror will develop and market high assurance system based on phase II development work and marketing plan from phase I. Offeror will achieve EAL6 or greater for high assurance computer system. Offeror will integrate high assurance hardware/OS system into an Army Aviation or Missile subsystem currently under development or via technology refresh. 

REFERENCES: 

1: [1] S. King, et al.: "SubVirt: implementing malware with virtual machines," IEEE Symposium on Security and Privacy, pp. 1-14, 21-24 May 2006.

2:  R. Fannon: An analysis of hardware-assisted virtual machine based rootkits, Thesis, Naval Postgraduate School, June 2014. calhoun.nps.edu/handle/10945/42621

3:  .G. Klein., et al.: "seL4: formal verification of an OS kernel," Proceedings of the ACM SIGOPS 22nd symposium on Operating systems principles, Big Sky, Montana, pp. 207-220, October 11 - 14, 2009.

4:  M. Lipp, et al.: "Meltdown," Cornel University Library, 3 Jan 2018. https://arxiv.org/pdf/1801.01207.pdf

5:  Darpa: "Baking Hack Resistance Directly into Hardware," 4/10/2017.

6:  A. Waterman, et. al. "The RISC-V Compressed Instruction Set Manual Version 1.9 (draft)" (PDF). RISC-V. https://riscv.org/wp-content/uploads/2015/11/riscv-compressed-spec-v1.9.pdf

7:  http://parallel.princeton.edu/openpiton/index.html#infosec.

8:  8: G. Klein., et al.: "seL4: formal verification of an OS kernel,"Proceedings of the ACM SIGOPS 22nd symposium on Operating systems principles, Big Sky, Montana, pp. 207-220, October 11 - 14, 2009.

9:  9: R. Smith, "A Contemporary Look at Saltzer and Schroeder's 1975 Design Principles", IEEE Security & Privacy, Vol. 10, No. 5, pp. 20-25, Nov.-Dec. 2012

10:  10: P. Jungwirth, et al.: "Cyber defense through hardware security", Proc. SPIE 10652, Disruptive Technologies in Information Sciences, 106520P (9 May 2018)

11:  doi: 10.1117/12.2302805

12:  https://doi.org/10.1117/12.2302805

13:  11: T. Nakano: "Hardware Implementation of a Real-time Operating System," IEEE TRON Project International Symposium, Tokyo, Japan, pp. 34-42, 28 Nov - 2 Dec 1995

14:  12: https://www.renesas.com/en-us/products/factory-automation/multi-protocol-communication/r-in32m3-hardware-rtos.html

15:  13: M. McCoyd, et al.: "Building a Hypervisor on a Formally Verifiable Protection Layer," https://people.eecs.berkeley.edu/~mmccoyd/papers/minvisor-hicss-12.pdf

16:  DARPA, "Clean-slate design of Resilient, Adaptive, Secure Hosts (CRASH)," DARPA-BAA-10-70, June 2010. https://www.fbo.gov/index=opportunity&mode=form&id=4022d960a15e87bcaf0fb70101ab53b8&tab=core&_cview=1

17:  15: J. Alves-Foss,et al.: A New Operating System for Security Tagged Architecture Hardware In Support of Multiple Independent Levels of Security (MILS) Compliant Systems, University of Idaho, Center Secure and Dependable Systems, Air Force Research Lab Tech Report AFRL-RI-RS-TR-2014-088, APRIL 2014.

18:  16: J. Song, and J. Alves-Foss. "Security tagging for a zero-kernel operating system." System Sciences (HICSS), 2013 46th Hawaii International Conference on. IEEE, 2013.

19:  R. Shioya, et al.: "Low-Overhead Architecture for Security Tag," IEEE Pacific Rim International Symposium on Dependable Computing, pp. 135-142, Shanghai, China, 16-18 Nov. 2009

20:  18: P.Jungwirth, et al.: "Hardware Security Kernel for Cyber Defense," SPIE Defense + Security Conference, Baltimore, MD, April 2019.

21:  http://www.defenseinnovationmarketplace.mil/resources/JMR_AMRDEC01.pdf

KEYWORDS: Assurance, Cyber Resilience, Embedded Systems, Trusted Computing, State Machine 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop and demonstrate a practical lightweight system for an on wing cryogenic liquid production system applicable to airborne thermal loads, and suitable for implementation on future US Army rotorcraft. 

DESCRIPTION: Emerging aircraft concepts are calling for increased electrical power and in many cases all electric aircraft designs. While accommodating the electric power requirement is a challenge in and of itself, thermal management of the components for the system becomes a priority engineering challenge as well. Cooling technology needs for these aircraft architectures are driven by the power and cooling demands of aircraft components such as superconducting motors/generators, Directed Energy Weapons (DEWs), and high powered jammers. From a military perspective high pulse power loads devices, such as DEWs, offer significant opportunities, as well as challenges, compared to traditional kinetic weapons. Airborne DEWs could perform a variety of Army missions including missile defense, counter-UAV operations, suppression of enemy air defenses, precision strike, etc. Although not limited to high energy lasers (HELs), the challenge of integrating such a device into a mission equipment package (MEP) illustrates the technical challenges ahead. HELs do not consume ammunition in the traditional sense, though they do consume significant amounts of electrical power. Lasers are intrinsically inefficient, and the “wall plug” efficiency can be considerably less than 50%. This means that to fire a 50 kW laser, 100 kW of electrical power would be needed. In addition, the net 50 kW of waste heat that is rejected to fire the laser must also be cooled which requires a cooling device that adds more size, weight, and power (SWaP). Typically the laser itself has tight thermal constraints which limit temperature changes to +/- 1° Celsius. Additionally, operating temperatures of the device are close to the operating temperatures of the external ambient air. The low quality heat is extremely difficult to move around. Therefore, significant incentive exists to maximize the efficiency of airborne DEWs to minimize both power and thermal management requirements. One way to enhance the efficiency of a laser is to cool it and operate the laser at cryogenic temperatures. Research has shown that wall-plug efficiency in excess of 70% is possible for cryogenically cooled solid-state lasers using liquid nitrogen (LN2). An airborne DEW operating at this efficiency would have significantly reduced power and thermal management requirements, but these benefits are only possible if the system is cryogenically cooled. For a cryogenic cooling system to be attractive, the benefits of increased efficiency must outweigh the cost, complexity and SWaP penalties associated with its implementation. If successfully developed, a low weight cryogenic liquid generator could be applied to a cooling system for superconducting motor/generators, high powered jammers, and/or HEL type devices. Metric goals and characteristics for the on-wing cryogenic liquid generator are as follows. The ratio of the amount of liquid cryogen produced per day to the device weight ((liters/day)/kg) should be greater than 1; with higher ratios being consequentially more desirable. For close looped systems assume the system has already been chilled and/or the reservoir is available. Production (cooling capability) goal is greater than or equal to 100 liters/day. Weight of the production equipment should not exceed 250 kg; weight is highly valued on a rotorcraft, hence any that can be removed should be. Operational ceiling is up to 5500 meters; performance must be characterized over the operational range. Temperatures up to 50 Celsius should be considered. If bleed air from an aircraft engine or secondary power unit (SPU) is required in the design, limit the bleed flow to a maximum .45 kg/sec (1 lb. /sec). Electrical power to drive equipment can assume 270VDC and an allotment of up to 40 kW of electrical load. Note, this system is not limited to LN2, innovative concepts which use any low temp fluid will be considered, such as, but not limited to liquefied natural gas (LNG), Ammonia, liquid ethylene, etc. 

PHASE I: Develop a design for a cryogenic liquid generator which meets or exceeds the aforementioned specifications. Utilization of models, and a systems engineering perspective is encouraged. 

PHASE II: Develop and demonstrate the critical components of the cryogenic liquid generator through prototyping and laboratory component/system testing. 

PHASE III: Phase III options would include development of a fully-functional prototype that could be used for cryogenic DEW ground and flight testing. For dual us applications the same technology could also be applied for other ground, naval, and airborne thermal management applications such as cooling superconducting systems including high-efficiency, compact motors and generators and lightweight power distribution systems. 

REFERENCES: 

1: J. P. Perin, et al., "Cryogenic Cooling For High Power Laser Amplifiers", IFSA 2011 - Seventh International Conference on Inertial Fusion Sciences and Applications, Bordeaux, France.

2:  R. Paschotta, article on 'cryogenic lasers' in the Encyclopedia of Laser Physics and Technology, 1. Edition October 2008, Wiley-VCH, ISBN 978-3-527-40828-3

3:  Rodger W. Dyson, "Novel Thermal Energy Conversion Technologies for Advanced Electric Air Vehicles"

4:  Scheidler, Justin J. PhD., "Preliminary Design of the Superconducting Rotor for NASA’s High-Efficiency Megawatt Motor. AIAA Propulsion and Energy Forum. July 9-11, 2018.

5:  "U.S. Army Weapons-Related Directed Energy (DE) Programs: Background and Potential Issues for Congress", Congressional research Service Report R45098 (2018).

6:  Vretenar, N., et al., "Cryogenic Yb:YAG Thin Disk Laser", AFRL Technical Paper AFRL-RD-PS-TP-2016-0004 (2016).

KEYWORDS: Directed Energy Weapons, Auxiliary Power Unit, Thermal Management, Cryogenic Cooling 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop novel muzzle brake structures for extended range cannon artillery systems that reduce mass and manufacturing cost, while maintaining or improving recoil reduction, signature management, durability, and operator safety. 

DESCRIPTION: Given the Army’s Long Range Precision Fires priority, a need exists for novel and innovative muzzle brakes capable of supporting the new extended range cannons. These include but are not limited by munitions currently under development for direct and indirect fire missions. High pressure produced at muzzle exit have negative impact upon the surrounding environment due to muzzle blast flow fields exiting the barrel. The negative consequences, such as recoil and noise production, can be alleviated by redirecting propellant gases. Muzzle brakes have been used for decades to efficiently redirect propellant gas, resulting in effective performance gains. However, recent advances in materials and additive manufacturing techniques show promise for muzzle brake weight reduction and manufacturing cost while maintaining the favorable flow field response and resistance to the resulting thermal and pressure loading. Muzzle brakes are subject to complex loading due to high exit pressure and gas momentum from the projectile emersion from the gun tube. Conditions at muzzle exit are dynamic and vary based on multiple factors. Typical pressure and thermal conditions have been found to be as much as 10-12 ksi and 2000 K, respectively. Gas flow has been found to be as high as 1,500 m/s and may contains small particles, such as solid propellant grains that did not undergo combustion. The muzzle environment can cause erosion on the brake surfaces. The shape of the muzzle brakes often consists of complex three dimensional curves and multiple openings. Examples of various muzzle brakes over the last century can be found in the references. Due to the harsh environment, material performance requirements, and complex shapes muzzle brakes used in current artillery systems are made of cast/forged steel. This topic seeks to develop novel applications of advanced materials, coatings and manufacturing technologies to muzzle brakes. A variety of analyses and tests should be done to show that the materials can survive the environment and that the manufacturing process can produce the complex shapes required. The objective for this effort is to achieve 30 percent weight reduction with either comparable or reduced cost compared to conventional steel muzzle brakes. 

PHASE I: Evaluate various material and coating combinations for use in the muzzle brake environment. Investigate manufacturing technologies such as additive manufacturing for combination with promising materials and coatings. Reference 1 (AMCP 706-251), section 3-3.2 provides an example of an open muzzle brake that can be used as a baseline. Conduct an analysis of alternatives to select the best combination of materials and manufacturing for prototypes to be delivered in Phase II. Select a candidate shape for Phase II. Reference 4 (US Patent No 8,424,440) for a 105mm gun is the preferred shape but other 105mm or 155mm shapes may be used with TPOC concurrence. Perform a preliminary validation of the manufacturing concept, and prepare initial production cost estimates for the designs under consideration. 

PHASE II: Subject promising material / coating combinations identified in Phase I to tests that simulate live fire conditions. Perform feasibility trials on the production of the muzzle brake design selected in Phase I. Produce at least one prototype muzzle brake using the selected final material / coating / manufacturing combination. Subject “as manufactured” sections of the prototype to simulated firing conditions to assess as manufactured performance. Perform final design refinements. Document final material, coating, and manufacturing process. 

PHASE III: Conduct a live fire demonstration of the final prototype in an operational environment with involvement from the prime contractor for the weapon system. Explore potential small arms applications for both military and private sector customers. 

REFERENCES: 

1: Headquarters, U. S. "Army Materiel Command," Engineering Design Handbook: Guns Series

2:  Muzzle Devices" AMC Pamphlet, Document No." (1968): 706-251. (https://apps.dtic.mil/dtic/tr/fulltext/u2/838748.pdf)

3:  Carlucci, Donald E., and Sidney S. Jacobson. Ballistics: Theory and Design and Ammunition. CRC Press, 2018.

4:  Schlenker, George. Contribution to the Analysis of Muzzle Brake Design. ROCK ISLAND ARSENAL IL, 1962. (https://apps.dtic.mil/dtic/tr/fulltext/u2/276154.pdf)

5:  Carson, Robert, and Christopher Aiello. "Low blast overpressure muzzle brake." U.S. Patent No. 8,424,440. 23 Apr. 2013.

6:  Smith, Morris Ford. "Gun." U.S. Patent No. 817,134. 3 Apr. 1906.

7:  Scheider, Eugene. "Prance." U.S. Patent No. 1,363,058. 21 Dec 1920.

8:  August, Bauer. "Silencer and recoil reducer for firearms." U.S. Patent No. 2,457,802. 4 Jan. 1949.

9:  Emilien, Prache Jacques. "Muzzle recoil check for firearms." U.S. Patent No. 2,567,826. 11 Sep. 1951.

10:  Thierry, R. "Muzzle attachment for reducing the recoil and blast effect of guns." U.S. Patent No. 3,714,864. 6 Feb. 1973.

11:  Ledys, Francis, and Jacques Bachelier. "Muzzle brake for weapon barrel." U.S. Patent No. 6,216,578. 17 Apr. 2001.

12:  Franchino, Anthony R., and Thomas Tighe. "Radial-venting baffled muzzle brake." U.S. Patent No. 6,578,462. 17 Jun. 2003.

13:  Bounds, Roger. "Lateral projection muzzle brake." U.S. Patent No. 7,032,339. 25 Apr. 2006.

14:  Poff, Charles. "Firearm muzzle brake." U.S. Patent No. 7,530,299. 12 May 2009.

KEYWORDS: Muzzle Device, Muzzle Brake, Manufacturing, Artillery, Cannon 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop a system to aggregate friendly force small arms fire control data to compute and display which individual or team has the highest probability of successfully engaging a target. 

DESCRIPTION: This effort supports the Army Modernization Priority of Soldier Lethality. Smart, networked small arms fire control systems are increasingly commonplace, especially with the proliferation of smartphones. Devices like the Kestrel Weathermeter[1] and the Sig Sauer KILO2400ABS laser rangefinder [2] have the capability to communicate with devices like smartphones to share data on environmental conditions, the weapon itself, and ammunition. These capabilities allow users to quickly create and edit ballistic inputs to maximize effects. In addition, there are techniques [3] that have been developed to compute the probability of hit for a small arms weapon system based upon the uncertainty in parameters like range to target, muzzle velocity, and wind speed. These techniques allow a user to provide a performance estimate for a weapon system given its ballistic parameters and the user's ability to measure and control the other factors that affect the flight of a bullet. By developing a method to connect the fire control systems to a centralized probability of hit calculator, this topic seeks to provide unit commanders with the capability to determine which asset at his disposal (e.g. infantry with an M4 or a sniper with an M110 and a laser rangefinder) would best be able to engage a given target. This would not be based only on user-provided information but would tie in actual measurements from sensors like weather meters, laser rangefinders, and weapon-mounted displays. Target/enemy information, such as enemy position and threat type, could be provided to the calculator from any number of sources, e.g., radar or individual user input. This data will provide the most accurate picture of friendly units' ability to engage threats. The integration of this data would enable a commander to evaluate the impact of moving units and threats around on a map, and to evaluate how the firing solutions and P(hit) calculations change, allowing him to determine which unit should engage each target to maximize the probability of successfully neutralizing the enemy. 

PHASE I: The objective of Phase I is to develop a system architecture and methodology for aggregating fire control data over a generic network that enables the data to be transferred and shared among systems. Document the proposed solution. Demonstrate software that couples simulated data from multiple sources with target profiles to compute a firing solution and probability of hit for each friendly asset. 

PHASE II: Phase II will build on a successful Phase I demonstration to connect physical devices to the probability of hit application and develop a user interface that presents the information on a map. The map should factor local terrain into the firing solution. The application should allow the input of enemy locations from users or from other sources. Demonstrate the capability to concurrently connect over 50 devices to the network and display their computed performance probabilities based upon the entered enemy parameters. 

PHASE III: This technology can be provided to law enforcement to help in deployment of their units in counter-sniper applications. This capability could be extended to other types of munitions, such as vehicle mounted weapons or indirect fire weapons, to help commanders better plan positioning of the units. There is also the potential for this capability to be used in the commercial market, allowing hunters to determine the best place to set up for engaging targets. 

REFERENCES: 

1: H. Chen, "Research on multi-sensor data fusion technology based on PSO-RBF neural network," 2015 IEEE Advanced Information Technology, Electronic and Automation Control Conference (IAEAC), Chongqing, 2015, pp. 265-269. doi: 10.1109/IAEAC.2015.7428560

2:  http://www.nkhome.com/support/kestrel-support/kestrel-software-and-apps/kestrel-link-ballistics-for-android/

3:  https://www.sigsauer.com/store/kilo2400abs.html

4:  http://www.appliedballisticsllc.com/Articles/ABDOC115_ProbabalisticWEZ.pdf

5:  https://www.google.com/url?sa=t&rct=j&q=&esrc=s&source=web&cd=2&cad=rja&uact=8&ved=2ahUKEwj2rIKW29beAhURu1MKHebEBdgQFjABegQIBRAB&url=https%3A%2F%2Fieeexplore.ieee.org%2Fiel7%2F7422354%2F7428505%2F07428560.pdf&usg=AOvVaw0vHHR2xHluj7W8I7NB-y_F

KEYWORDS: Small Arms, Fire Control, Networked, Probability Of Hit, Sniper 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Increase the through thickness modulus of carbon fiber thermoplastic composites through the use of nano-additives. These composites are used on large caliber direct and indirect fire gun tubes. They use polyetheretherketone (PEEK) as the thermoplastic matrix and are processed via fiber placement. The increase in the through thickness modulus should not decrease the in-plane properties of the composite nor the ability to process it via fiber placement. 

DESCRIPTION: There is a need to increase the through thickness modulus in fiber placed thermoplastic composites. These materials are being used to overwrap gun tubes for both direct and indirect fire and the effectiveness of the composite wrap is limited by the through thickness modulus. Traditionally this modulus is only that of the matrix material which is an order of magnitude or more lower than that of the reinforcement. On previous efforts it was found that after about 0.5 - 0.75 inches of overwrap adding additional material doesn't help with limiting bore dilation due to the low modulus in the radial direction being solely a function of the matrix. This effort focuses on developing a process to increase the through thickness modulus by adding nano-materials to the matrix. The addition of these materials should not be detrimental to the in plane properties of the base composite and should still be processable via fiber placement. 

PHASE I: Develop a process to increase the through thickness modulus of carbon fiber reinforced thermoplastic by adding nano-materials to the system. For this effort the baseline material is the fully unidirectional carbon fiber / polyetheretherketone (PEEK) system commonly referred to as IM7/PEEK. This material is processed via fiber placement using either hot gas torches or lasers as the heating source. The material is processed as a fully consolidated tape of IM7/PEEK. A study should be conducted as to what type / loading amount of nano-material will give the highest increase in through thickness modulus without degrading in plane properties or processability. A suggested method for measuring the through thickness modulus is ASTM D695 with two to one size anisotropy though other methods are acceptable. The threshold is a 75% increase in through thickness modulus over the baseline of pure PEEK. The objective is a 200% increase. The material deliverable is the equivalent of one square meter (can be of any width) of the improved material for testing. The material deliverable does not have to be in a form processable by fiber placement but should be processable by heated platen press or autoclave. 

PHASE II: Refine the process and improve the modulus results over Phase I. Minimum expected improvement is 100% over pure PEEK with an objective of 200% or more increase. Material must be processable via fiber placement. The as processed interlaminar shear strength (D2344 -Standard Test Method for Short-Beam Strength of Polymer Matrix Composite Materials and Their Laminates), shall be equal to or greater than 9 ksi and any deviation from this value shall be reported and a plan to achieve 9 ksi shall be described. No degradation of the in-plane properties shall be verified by conducting at a minimum ASTM D3039 (Standard Test Method for Tensile Properties of Polymer Matrix Composite Materials) in both longitudinal and transverse directions. Thermal conductivity shall also be measured to determine if there is any increase over the baseline material. The material deliverable is 25 lbs of 1/2" wide material capable of being processed via fiber placement. 

PHASE III: Finalize the development of a material based solution at production level quantities that can be readily implemented on existing manufacturing equipment. Non-DoD applications include down well piping, engine components, etc. 

REFERENCES: 

1: J. B. Root and A. G. Littlefield, Minimizing Rail Deflections in an EM Railgun, November 2006. http://handle.dtic.mil/100.2/ADA481582

2:  R. M. Erb, R. Libanori, N. Rothfuchs, A. R. Studart, "Composites Reinforced in Three Dimensions by Using Low Magnetic Fields," Science, Vol 335, 13 Jan 2012, pp 199-204

3:  L. Burton, R. Carter, V. Champagne, R. Emerson, M.l Audino, and E. Troiano, Army Targets Age Old Problems with New Gun Barrel Materials, AMPTIAC Quarterly, v8n4, 2004. http://ammtiac.alionscience.com/pdf/AMPQ8_4ART08.pdf

4:  A. Littlefield and E. Hyland, Prestressed Carbon Fiber Composite Overwrapped Gun Tube, November 2006. http://handle.dtic.mil/100.2/ADA481065

5:  S. Montgomery and R. L. Ellis, Large Caliber Gun Tube Materials Systems Design, 10th U.S. Army Gun Dynamics Symposium Proceedings, Austin, TX, April 2002. http://handle.dtic.mil/100.2/ADP012479

6:  U.S. Army Materiel Command, "Research and Development of Materiel, Engineering Design Handbook, Gun Series, Gun Tubes," AMCP 706-252, Washington DC (1964). http://handle.dtic.mil/100.2/AD830297

7:  Office of the Secretary of Defense (OSD) Manufacturing Technology Program, Manufacturing Readiness Level (MRL) Deskbook, Version 2.0, May 2011. http://www.dodmrl.com/MRL_Deskbook_V2.pdf

8:  J. B. Root, V. Olmstead, A. G. Littlefield, K. Truszkowska, "An Analysis of EM Railgun Cross Section Designs," ARDEC Technical Report ARWSB-TR-09017, Aug 2009, http://www.dtic.mil/docs/citations/ADA593788

9:  W. Zhang, J. Suhr, N. Koratkar, "Observation of High Buckling Stability in Carbon Nanotube Composites", Advanced Materials, Vol 18, 4, 2006, 452-456.

10:  M.A. Rafiee, J. Rafiee, Z. Wang, H. Song, Z.Z. Yu, N. Koratkar, "Enhanced Mechanical Properties of Nanocomposites at Low Graphene Content", ACS Nano, 3 (12), 2009, 2884-3890

11:  M.A. Rafiee, J. Rafiee, Z. Wang, H. Song, Z.Z. Yu, N. Koratkar, "Enhanced Mechanical Properties of Nanocomposites at Low Graphene Content", ACS Nano, 3 (12), 2009, 2884-3890

KEYWORDS: Advanced Composites, Nanomaterials, Fiber Placement, Thermoplastic Composites 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Investigate and develop innovative solutions to enable integration of electronic warfare antennas on munition launched rounds. Antenna systems must be capable of surviving a typical mortar gun launch and maintaining their operational performance throughout flight. 

DESCRIPTION: Recent advancements in high-shock, munition-launched compatible electronics technology particularly have opened up a wide realm of possibilities for enabling long-range and inexpensive electronic warfare attacks of ground targets via relatively inexpensive munition launched systems and projectiles. To enable this mission, projectiles must be equipped the associated electronics and RF sensors. Due to the highly constrained volume and structural integrity requirements, these sensors must be conformal to the outer mold line with very minimal intrusion into the structural wall of the projectile. Surface area on these projectiles is also very limited; therefore, these sensors must be small, residing within the allotted payload space. It is also requisite that the sensor operates over several ISM bands, while providing omni-directional beam pattern coverage. All this must be performed at shock loads approaching 20,000 g’s. Army is looking for novel advancements in conformal antenna technology to enable this mission set on a range of prospective gun-launched platforms (e.g. mortars and artillery). Aperture designs should be innately scalable to accommodate different munitions with tuneable frequency characteristics and incorporate knowledge and understanding of relevant high-shock compatible materials and construction techniques. A critical aspect of the effort involves that the apertures are insensitive to large changes in response due to the large shock loads experienced during launch. Furthermore, designs should incorporate knowledge and understanding of miniaturization techniques, while still achieving the objective bandwidth and pattern coverage requirements. 

PHASE I: During the Phase I contract, successful proposers shall conduct a proof of concept study that focuses on the feasibility of designing the antenna apertures. Investigations should include analysis of potential aperture mounting configurations, achievable antenna performance (gain, bandwidth, pattern coverage), and materials capable of surviving the expected environments. Verification of RF performance shall be accomplished through simulation and prototype antenna measurements. A final proposed concept design, including a detailed description and analysis of both expected thermal and mechanical loads, is expected at the completion of the Phase I effort. 

PHASE II: If selected for a Phase II, the proposer shall fabricate and integrate the prototype antenna apertures into a nominal projectile form-factor. The proposer shall further their proof of concept design by performing component shock and thermal testing on critical components/connections of the aperture. Special emphasis on launch survivability will be required, including hard force and electromagnetic effects during testing to ensure the apertures can avoid failure or degradation. Upon evaluation of the design through a critical design review, the prototype hardware’s survivability shall be demonstrated through either air-, chemical-, or munition launches. Information and data collected from the flights will be used to validate operational electrical performance. 

PHASE III: Phase III selections shall ruggedized final design, fabricate it and integrate the prototype antenna apertures into nominal projectile form-factor to be identified by the Government. Live fire tests will be conducted and the antenna integrated with projectile form-factor will have to withstand shock load approaching 20,000g’s. Phase III selections might have adequate support from an Army prime or industry transition partner identified during earlier phases of the program. The proposer shall work with this partner (TBD) to fully develop, integrate, and test the performance and survivability characteristics of the design for integration onto the vendor’s target platform. COMMERCIALIZATION: Robust, high-shock antenna components are continually in demand by the aerospace and chemical / petroleum industry. Further commercial applications include civilian space-flight initiatives and application of the antenna technology for the design of low-cost, high-temperature, high-shock antenna sensors. 

REFERENCES: 

1: Grzybowski, David M., Philip J. Peregino, and Bradford S. Davis. Development of a Telemetry-Enabled High-G Projectile Carrier. No. ARL-TR-6099. ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE, 2012. http://www.dtic.mil/dtic/tr/fulltext/u2/a568926.pdf

2:  US Army Test and Evaluation Command Operations Procedure, "Projectile Velocity Measurements" (Top 4-2-805) http://www.dtic.mil/dtic/tr/fulltext/u2/a119554.pdf

3:  M120 Mortar System, https://en.wikipedia.org/wiki/Soltam_K6

4:  http://en.wikipedia.org/wiki/Mortar_(weapon).

5:  https://en.wikipedia.org/wiki/M777_howitzer

KEYWORDS: Antenna, Electronic Warfare, Projectile, Munition, Mortar, Artillery, Sensors 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Design and develop an optimization algorithm to provide persistent coverage of an area of interest by swarms of assets for target acquisition and engagement. 

DESCRIPTION: This effort aims to provide a significant capability to the Soldier Lethality CFT by increasing data accuracy during the direct fire engagement process for digital soldiers. This topic will also develop swarming technologies that can be integrated into NGCV for targeting and engagement; specifically by utilizing augmentation of LOS/BLOS NGCV fires and effects integrated with upper-echelon systems for cooperative engagement, as well as the integration of fires and maneuver to achieve tactical overmatch. Current technologies should allow the development an optimized solution to cover a predetermined area of interest by the swarms of combined assets in the persistent way. In particular, this coverage will involve both mobile and stationary target acquisition and engagement assets. Some of these assets may be weaponized to engage the targets. The route patterns of moving assets can be assumed to be fixed in order to satisfy the persistent surveillance requirement. Also, periodic maintenance and refueling/recharging must be addressed. For stationary assets, the maintenance requirements may be significantly relaxed since the power consumption of these assets can be significantly reduced. The algorithm must also account for the possibility that assets may have the capability to fly and perch on the wall of the building, inside a cave or tunnel, on the trunk of a tree, or on other structures depending on the asset’s size, weight, and other factors. These assets might geolocate the targets and serve as potential forward observers for engaging the targets. The optimized solution should rely as much as possible on autonomy to enable assets capable to return to their place(s) of origin on with minimal communication both among assets with the operator unit controller (OUC). Special attention should also be paid to assure the collision avoidance among assets. 

PHASE I: Design and develop innovative state-of-the-art software optimization algorithm for the persistent coverage of a predetermined area of interest by the swarms of assets capable of autonomous navigation. Model the algorithm’s performance with data supply by assets with “fly and perch” capability. Demonstrate how the proposed algorithms will optimize the coverage provided by assets in a dynamic threat environment. 

PHASE II: Develop and demonstrate a prototype capability with swarms of at least six assets autonomously navigating over a predetermined area of interest using the developmental offline software algorithms. The collaborative assets should be demonstrate the capability of autonomous return to their points of origin. The prototype should demonstrate assets’ ability to transition to the forward observer state from the perching and dormant states based on the appropriate input triggers to initiate collaborative target engagement. This prototype should be capable of integrating with CCDC Armaments Center supplied fires and effects architecture. Conduct testing to demonstrate feasibility of this technology for operation within a simulation environment operated by CCDC Armaments Center. 

PHASE III: CCDC Armaments Center swarming/perching technology developed under this effort should have open architecture allowing it to be easily integrated with the tactical decision support systems and to enable swarming munition technologies. Department of Homeland security could use this capability to monitor the illegal crossings of the US borders. In addition, SOCOM could use this technology for surveillance of terrorist activities in urban places, while FBI/CIA could use it for intelligence gathering. 

REFERENCES: 

1: Z.R. Bogdanowicz, "Swarm of autonomous unmanned aerial vehicles with 3D deconfliction", Proc. SPIE 10651, Open Architecture/Open Business Model Net-Centric Systems and Defense Transformation 1018, 106510L (9 May 2018), SPIE Defense + Security, 2018, Orlando, Florida. .

2:  Z.R. Bogdanowicz, "Flying swarm of drones over circulant digraph", IEEE Transactions on Aerospace and Electronic Systems, Vol. 53, No. 6, 2662-2670, 2017.

3:  Y. Cao, W. Yu, W. Ren, and G. Chen, "An overview of recent progress in the study of distributed multiagent coordination", IEEE Transactions on Industrial Informatics, Vol. 9, no. 1, 427-438, 2013.

4:  Z. Chen, M. C. Fan, and H. T. Zhang, "How much control is enough for network connectivity preservation and collision avoidance?", IEEE Transactions on Cybernetics, Vol. 45, No. 8, 1647-1656, 2015.

5:  B. Fidam, V. Gazi, S. Zhai, N. Cen, and E. Karatas, "Single-view distance-estimation-based formation control of robotic swarms", IEEE Transactions on Industrial Electronics, Vol. 60, No. 12, 5781-5791, 2013.

6:  J. H. Son and H. S. Ahn, "Formation coordination for propagation of group of mobile agents via self-mobile localization", IEEE Systems Journal, Vol. 9, No. 4, 1285-1296, 2015.

KEYWORDS: Perching, Autonomous UAV/UGV, Swarm Of UAVs/UGVs, Forward Observer, Target Engagement, Weaponized UAVs/UGVs 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop novel multifunctional materials for the next-generation munitions for the long range precision fire (LRPF) program under the Army Modernization effort to provide increased lethality and impose superiority on contested and expanded battlefield. 

DESCRIPTION: With the evolution of modern battlefields, the Army is seeking a new generation of munitions to overmatch, deter and disrupt its adversaries. The next-generation of weapons aims to provide an increased kinetic advantage over increasingly complex targets, situations and at longer distances. The development and implementation of such systems will require new multifunctional materials and components with advanced effects to maintain and further extend our troops’ superiority. The increased complexity of munitions, where target identification and guidance systems now occupy a larger portion of the warhead, has been made at the expense of the payload. The integration of reactive materials has been identified and demonstrated as a method to restore lethality by increasing the overall energy output of these enhanced munitions and improving system effectiveness. However, the integration of these materials has been limited by their mechanical properties. This topic aims at further expanding the field of structural reactive materials (SRM), where a portion of the traditional ordnance is replaced with an SRM. Such multi-purpose components offer opportunities to integrate materials of high strength and density that adds additional damage mechanism to defeat the target. The objective of this program is to develop novel SRMs with mechanical properties and density similar or superior to munition-grade steel, and capable of providing an energetic output upon initiation by detonation or high-velocity impact, while maintaining their integrity under the harsh launch conditions and flight loads resulting from the next-generation guns. Focus should also be given to the establishment of novel processing methods to ensure the rapid transition of the proposed technology into new or existing weapon systems. This proposal shall develop and demonstrate the properties of these multifunctional materials in comparison with established inert materials. The characterization will include mechanical properties such as tensile and compression strength, density and hardness. The energetic performance of the novel SRM will be characterized by experimental testing to measure energy release and warhead fragmentation 

PHASE I: Develop at least one novel SRM with a density equivalent or superior to munition-grade steel. Perform characterization experiments to establish the mechanical, thermal and energetic performance of the SRM in comparison with baseline inert material such as munitions grade steel. The minimum requirements for mechanical properties are 100 ksi tensile strength and greater than 5% elongation, while the energy release should be greater than 1500 cal/g. Conduct small scale fabrication to show manufacturing feasibility. Provide material sample to the Army POC. 

PHASE II: Further develop and optimize the SRM established in Phase I using thermodynamic analysis to achieve the best combinations of mechanical and energy release properties. Characterize mechanical properties. Measure energy release and characterize warhead case fragmentation in small scale tests, such as blast chamber testing. Scale-up the manufacturing process and produce prototypes in at least 3 configurations of interest to the Army and deliver 5 prototypes from each configuration to the Army. 

PHASE III: Transition the developed materials and related technology to a major manufacturer for incorporating this technology into next-generation munitions for the long range precision fire (LRPF) program. To further exploit the benefits of the developed technology, form partnerships with other manufacturers for applications to the civil sectors, such as the oil well and construction industries. This technology can also be leveraged to mining applications as well as applications occur in submarine blasting, breaking log jams, breaking ice jams, initiating avalanches, timber or tree cutting, the perforation of arctic sea-ice or permafrost, glacier blasting, ice breaking, and underwater demolition. 

REFERENCES: 

1: P. Redner, D. Kapoor, C. Haines, D. Martin, J. Paras, R. Carpenter, B. Travers, J. Pham, Processing and Handling of Reactive and Structural Reactive Materials, AIChE Annual Meeting, 2009.

2:  R. Zaharieva, S. Hanagud, Preliminary design of multifunctional structural-energetic materials for high density, high strength and release of high enthalpic energy, International Journal of Scientific Engineering and Technology 3 (2014) 1189-1192.

3:  https://www.darpa.mil/program/reactive-material-structures

4:  https://www.worldscientific.com/doi/abs/10.1142/9789814317665_0022

KEYWORDS: Next-generation Munition, Structural Reactive Materials, High Strength Material, High Density Reactive Material, Novel Processing Methods 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop a methodology and build a prototype to quickly perform non-destructive corrosion testing of small arms ammunition components in the field prior to use by the warfighter or during the development of new energetic materials. 

DESCRIPTION: Energetic material advances have resulted in the development of several suitable lead-free replacements for lead styphnate and lead azide in munition formulations. These lead-free energetic materials could potentially create unexpected corrosive environments for traditional cartridge brass and other munition components. Further efforts to replace cartridge brass with novel lightweight and/or combustible cartridge cases creates additional unknown long-term reliability issues. Field testing of ammunition components is therefore critical in future deployments to assure weapon system effectiveness from the ammunition life cycle perspective, i.e. the time of production to the time of expenditure. Many field techniques are currently subject to a visual inspection of the small arms ammunition but recent advances in non-destructive metallurgical and material analysis allows for this inspection to be more analytically robust and time effective. This SBIR project provides the opportunity to employ these modern corrosion inspection techniques to be implemented for use in developmental stages of new energetic materials and in the field for a wide range of small arms ammunition components. 

PHASE I: Develop process validity and methodology for non-destructive inspection of modern explosives and munition housings on a lab scale. Identify, develop, and test likely lead-replacement candidates against likely substrates based on the published literature. Major considerations for the success of the feasibility study include the time of inspection and quality of the reported data. 

PHASE II: Based on the methodology established during the Phase I, a hand-held test cell prototype will be developed and certified to the appropriate Military standards, specifications, and UL requirements. This prototype test cell will incorporate appropriately designed small arms ammunition component tooling to provide an interface with different applications. A working prototype test cell with directions on its use will be delivered to the Program Executive Officer for Ammunition for field testing. 

PHASE III: If this program is demonstrated to be successful, this non-destructive inspection technique for modern explosives and ammunition housings can be used in both military and civilian applications. Military applications include small arms components (5.56mm, 7.62mm, and .50 calibers), explosive munitions (M42, M55, and M61 initiators), and medium caliber (20mm, 25mm, 30mm and 40mm), as well as, potentially large caliber (60mm, 81mm, 105mm, and 120mm) ammunitions. Civilian applications include hunting, sport shooting, and law enforcement. 

REFERENCES: 

1: Military Standard Practice MIL-STD-889C, Dissimilar Metals, revision C (DOD, 22 August 2016)

2:  Design Criteria Standard MIL-STD-1568C, Materials and Processes for Corrosion Prevention and Control in Aerospace Weapons Systems, revision C (DOD, 12 August 2014)

3:  Test Method Standard MIL-STD-1904B, Design and Test Requirements for Level A Ammunition Packaging, revision B, (DOD, 09 March 2016)

4:  Drobockyi, Volodymyr and Viggiano, Anthony, inventor

5:  Shell Shock Technologies, Inc. assignee. Method of Making a Casing and Cartridge for Firearm, US patent application 2017/0030692 A1. February 2, 2017.

6:  Natarajan R., Angelo P.C., George N.T., and Tamhankar R.V. 1974. Dezincification of Cartridge Brass. Corrosion. 31 (8): 302-303

7:  Hagel R., and Redecker K. 1986. Sintox – A New, Non-Toxic Primer Composition by Dynamit Nobel AG. Propellants, Explosives, Pyrotechnics. 11: 184-187

8:  Ostrowski P., Puszynski J., Bichay M. 2006. Nano Energetics for US Navy Percussion Primer Applications. AIChe Annual Meeting. San Francisco, CA

9:  Fischer D., Klapӧtke T., Stierstorfer J. 2014. Potassium 1,1’-Dinitramino-5,5’-bistetrazolate: A Primary Explosive with Fast Detonation and High Initiation Power. Angewadnte Communications, International Edition. 53: 8172-8175

10:  Fronabarger J., Williams M., Sanborn W., Bragg J., Parrish D., and Bichay M. 2011. DBX-1 - A Lead Free Replacement for Lead Azide. Propellants, Explosives, Pyrotechnics. 36: 541-550

KEYWORDS: Green Energetics, Small Arms Ammunition, Non-destructive Testing, Corrosion 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: The objective of this effort is to develop a small, low cost, optical based proximity sensor for fuzing applications. Once a proof-of-concept optical design is demonstrated, a cost model should be established, as well as a transition plan to bring the sensors into production. Emphasis during all phases of this project should be on developing a sensor with minimized cost and size. 

DESCRIPTION: Most current fielded proximity sensor today are RF based. With the increasingly cluttered RF environments, the need for different proximity sensor base technologies has been realized. A few key requirements for this sensor are volume <5cm^3, <150mW, -45º to +145ºF operating temperature, ability to survive high G environments (up to 50,000G), <$150 in production of 100k units per year. The targets of interest can range from indirect ground/water targets, to urban environments, along with direct fire engagements on small air targets. Standoff distances anywhere from 0.1m up to 20m could be possible. 

PHASE I: During Phase I, a feasibility study of the proposed sensor concept shall be conducted to provide evidence that demonstrates the concept can meet the stated requirements. This study should identify the equipment and resources needed to prototype a device, as well as initial device designs and unit cost estimates. 

PHASE II: Phase II shall begin by prototyping the initial sensor design and evaluating its performance against the stated requirements. It is expected that one or more design iterations will occur during the 2nd phase. Phase II will end with a proof-of-concept prototype that demonstrates the performance and producibility of the sensor through a gun fired test. Deliverables include quarterly progress reports, prototype hardware, a manufacturing plan, a field test and a final report. 

PHASE III: Phase III shall begin with the execution of the manufacturing plan developed in phase II. Continued development of the sensor shall be pursued to reduce manufacturing costs. Key military applications for these devices are for end game fuzing. This technology can be expanded to commercial applications including car safety awareness systems. 

REFERENCES: 

1: https://ndiastorage.blob.core.usgovcloudapi.net/ndia/2010/fuze/IIIASandomirsky.pdf

2:  http://www.dtic.mil/dtic/tr/fulltext/u2/a432853.pdf

3:  http://spie.org/newsroom/0066-advanced-optical-fuzing-technology?SSO=1

4:  https://en.wikipedia.org/wiki/Proximity_fuze

KEYWORDS: Fuze, Fuzing, Electronic, Diode, Optical, Laser 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Research innovative manufacturing processes to create reduced-weight components that can survive high temperature and high compressive (g loading) environments. 

DESCRIPTION: The US Army is in need of weight reduction for components used in gun-launched environments. In order to achieve the desired weight reduction, manufacturing processes other than the traditional subtractive types need to be explored. This project will investigate innovative materials, designs, and manufacturing methods to minimize production cost, minimize weight, and maintain the relevant performance requirements. Weight reduction of at least 50 percent as compared to the traditional component equivalent is the goal, while surviving long term temperatures storage requirements of up to 160 degrees Fahrenheit and short term instantaneous temperature exposure of 900 degrees Fahrenheit while surviving shock loading up to 45,000 g’s. Components can vary in both size and shape with a volume not to exceed 16.5 cubic inches. Specific design targets will be provided at project kickoff. 

PHASE I: Investigate the feasibility and cost effectiveness of various alternate manufacturing processes and material combinations capable of surviving the gun-launch environment while significantly reducing the weight of the identified components. Define and execute a modeling and simulation test plan that will optimize component designs and material selections, and inform on the decision to switch to new manufacturing processes as well as the associated business case to do so. The best value of material/process/time is the objective. Success of Phase I will be the measured by a 50% weight reduction compared to traditional manufacturing methods utilizing the same material. Submission of a cost analysis is required but will not be used as a measure of success for Phase I. 

PHASE II: Based on successful results of Phase I, develop, demonstrate, and fabricate a well-defined solution that is reproducible, and exhibits confidence in transition to both military and commercial markets. The objective is to conduct further development and optimization of the design and materials that provide the best balance to achieve the requirements, specifications, and metrics listed in this topic. The Phase II effort will significantly improve upon the performance and efficiency of the conceptual design developed under Phase I. This will include performance testing in the contractor’s facility as well as simulated environment testing at a government location. 

PHASE III: A full size prototype (drawings will be provided by the government for production of prototype component) of the best performer whose metrics include weight reduction, strength, and cost from Phase II will be delivered to the Government and integrated into a full-scale demonstration. A full TDP outlining the manufacturing process as well as material selection will be provided upon completion of Phase III. Commercial applications include automotive and aircraft engines. 

REFERENCES: 

1: Umetani and Schmidt (2013) Umetani N., Schmidt R.

2:  Cross-sectional structural analysis for 3d printing optimization

3:  Lu et al. (2014) Lu L., Sharf A., Zhao H., Wei Y., Fan Q., Chen X., Savoye Y., Tu C., Cohen-Or D., Chen B.

4:  Build-to-last: strength to weight 3d printed objects

5:  Stava et al. (2012) Stava O., Vanek J., Benes B., Carr N., Měch R.

6:  Stress relief: improving structural strength of 3d printable objects

7:  E. Jelis, M. Hespos and N. Ravindra, "Process Evaluation of AISI 4340 Steel Manufactured by Laser Powder Bed Fusion," Journal of Materials Engineering and Performance, vol. 27, no. 1, p. 63–71, 2017

KEYWORDS: Additive Manufacturing, Alternate Manufacturing Process, Light Weight, High Temperature, High Strength, 3D Printing, Metal Matrix, Alternate Materials 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Design and develop a precise gun-hardened miniature electronics sensor suite to provide precise position, acceleration, and velocity. 

DESCRIPTION: The US Army is in need of an on-board munition sensor package suite that provides the measurement capabilities of a three-axis gyroscope, a three-axis accelerometer, and a three-axis magnetometer. This innovative solution should have a footprint of 20mm x 20mm. The sensor package suite must be capable of surviving a minimum of 20,000 Gs. If the proposed solution relies on an external battery, the sensor package must operate on 3.7 volts with a maximum power consumption of 45 watts. A solution with a 20-year shelf life, EMI resistance, and compatibility with military operating and storage conditions is desired. 

PHASE I: The contractor shall investigate the feasibility of development of the sensor package and provide a trade-off analysis for the desired measurement capabilities, form factor, cost, and shelf life. The trade-off analysis must include alternate sensor specifications as well as any possible additions to the package for operational improvements. A preliminary sensor package design must be completed by the conclusion of phase I. 

PHASE II: The contractor shall provide the final design of two possible sensor packages based upon the outcome of Phase I along with input from US government. The final designs components that can be readily manufactured. After final designs have been agreed upon, one prototype of the fully assembled board for each design will be delivered for testing at a US government lab. Manufacturing partners should be engaged early in the phase II process to ensure manufacturability and to shorten the timeline for fielding. 

PHASE III: Four fully assembled boards will be provided to USG for final testing and verification. The final product will be based upon input from initial test results provided by USG to contractor from Phase II. The contractor will update the board layout and form factor based upon results from Phase II and government requirements for size. A final TDP package must also be delivered to the government as closeout of this phase. 

REFERENCES: 

1: Electronic Components for High-g Hardened Packaging

2:  Morris S. Berman

3:  Haleh Ardebili, Michael Pecht, Encapsulation Technologies for ElectronicApplications

4:  William Andrew, 2009 ISBN 0815519702 "What is Conformal Coating?".

5:  http://caution-www.electrolube.com/

KEYWORDS: Gyroscope, Accelerometer, Magnetometer, Sensor Package, Electronics 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Design, develop, prototype and demonstrate the ability to form an array of wide field of micro-lenses that can be directly printed down on a Complementary metal–oxide–semiconductor (CMOS) imager. These lenses can either be compound, Gradient Index (GRIN), Freeform, or other. The intent is use such an array in a light field optical configuration to yield a very thin, light camera package that is both fast and compact in size and weight. 

DESCRIPTION: The necessity for snipers, soldiers, and crew served weapons operators to rapidly and accurately detect targets on the battlefield is a capability that is of high interest to the department of defense, across all agencies. It is our desire to create a compact camera system that has a wide field of view as well as high resolution. Commercially we can find an exemplar in the Lytro approach. Other configurations can be found in “Spatio-Angular Resolution Tradeoff in Integral Photography” [T. Georgeiv et. al. Eurographics Symposium on Rendering, 2006). Any given micro-lens will have a very short focal length. We can make the focal length small robust if we form the lenses directly on the CMOS imager as suggested by Thiele et al. in Sci. Adv. 2017; 3:e1602655. The effective aperture is that of the array, It is expected that eventually these imagers/lens arrays will be further clustered to produce very large effective apertures. The clustered effective aperture need not be circular, but may be configured in such a way as to nest on a platform, such as a rifle. In such a case the aperture could wrap around the barrel, thus yielding not only a compact package, but one that would allow for passive ranging and three dimensional image reconstruction as well. 

PHASE I: Identify materials, methods and models integrated lens arrays that are compatible with CMOS imagers. Model the optical systems to ensure that the lenslet arrays will yield suitable image quality for later image reconstruction. 

PHASE II: Create an array on a CMOS imager. This imager should be functional and allow one to read out each of the sub-images. Transfer the readout into a computer and demonstrate that light field reconstruction is viable. Contractor shall clearly state in the proposal and final report how the phenomenology provides the unique capability for achieving the design goals. Make an array of the lenslet/CMOS imager modules and show that the subsampled synthetic aperture is functional. 

PHASE III: Optimize the physical properties for military applications. Prototype a rifle mounted fire control sight using this technology that demonstrates the benefits in performance over currently fielded systems. Replace conventional electro-optics with the design in a sight that represents the optical performance of a fielded military small arms sighting system. Test and report the results of the optical metrology/performance and weight savings. Create a partnership with industry to commercialize the technology and improve the manufacturability. The prototype will be TRL 4 at the end of phase III 

REFERENCES: 

1: "Spatio-Angular Resolution Tradeoff in Integral Photography" [T. Georgeiv et. al. Eurographics Symposium on Rendering, 2006).

2:  Thiele et al. in Sci. Adv. 2017

3:  3:e1602655

KEYWORDS: Conformal Optics 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop a 2-color mid and long-wave infrared (MidIR and LWIR) thermal polarimetric camera system with incorporated artificial intelligence and machine learning (AI&ML) capability for enhanced target detection and identification. 

DESCRIPTION: During the past decade two different technological areas have advanced significantly, i.e., thermal polarimetric camera systems and AI&ML capabilities for data analysis and exploitation. Currently, DoD spend many tens of millions of dollars per year developing and testing thermal sensor systems designed for 24/7 day/night surveillance capabilities for a wide variety of tactical scenarios, e.g., detection of buried landmines and IEDs, identification of camouflaged/hidden targets, and night-time facial recognition.[1-4] The advances in AI&ML are driven by new algorithms, notably deep neural networks (DNN), and the maturation of graphical processing unit (GPU) technology optimized for intensive matrix computations. The latest AI&ML algorithms can be trained relatively quickly on low cost GPUs to perform inference on GPUs in real-time. In particular, deep convolutional neural networks (CNN) have demonstrated their potential for accurate object detection and classification. [5-8] In order to exploit these advances in polarimetric imaging and AI&ML, we propose the development of an “integrated” multimodal thermal imaging and data exploitation system designed to provide “real-time” scene understanding and situational awareness. Such a system would greatly reduce the time and cost required to bring soldier specific image based solutions to the battlefield. To provide 24/7 day/night operation we limit the image modalities to be considered to a 2-color (MidIR and LWIR) polarimetric image system.[9-11] Assuming 2-color polarimetric operation, the possible image modalities are the conventional thermal images in each band, S0(MidIR) and S0(LWIR) and their polarimetric counterparts, i.e., Stokes images, S1 and S2 in each band, i.e., S1(MidIR), S2(MidIR), S1(LWIR), S2(LWIR). Additional modalities to be considered are various linear/non-linear combinations of the aforementioned Stokes images, e.g., degree-of-linear polarization (DoLP) image in each band, DoLP(MidIR), DoLP(LWIR). This image stream is expected to be analyzed in real-time by the AI&ML algorithms in order to produce maximum situational awareness. As a result, this system is expected to provide unprecedented target/anomaly detection performance for a large variety of DoD related applications. 

PHASE I: During the initial solicitation candidates must identify 1) the optical design proposed for the 2-color polarimetric camera system, and 2) hardware, architecture, and algorithm(s) for the AI&ML operation of the system. As a result, during the Phase I candidates will be expected to conduct a feasibility study which will consist of predictive analysis and/or preliminary prototype development in support of their proposed polarimetric/AI&ML design. This should include identifying and assessing (with costs) all critical components necessary to develop the proposed system. Specifically, the candidate should define and identify particular focal-plane-array (FPA) architecture, readout circuitry, minimum integration time, optical design, spectral responsivity, and control/analysis hardware and software required for high resolution, high frame-rate operation. Analysis should include optical design modeling and optimization in which both radiometric and polarimetric response characteristics are predicted, e.g., expected noise-equivalent-delta-temperature (NEDT), and noise-equivalent-delta-polarization state (NEDP). 

PHASE II: Based on the design criteria established during the Phase I, the candidate will procure all necessary components in order to assemble, test, and demonstrate a fully functional prototype device. Initial prototype development and testing will include both laboratory and field-based assessment in which standard image quality metrics will be determined, e.g., modulation-transfer-function (MTF), NEDT, and NEDP. Testing will also include evaluation of various AI&ML algorithms based on specific test objectives, e.g., anomaly detection of hidden targets within a high clutter urban environment. Prototype testing and evaluation will be conducted at a government facility in which optimum functionality will be determined based on range, atmospheric conditions, and tactical scenario. To be conducted concurrent with the prototype development, the contractor will begin identifying all possible commercialization opportunities and partnerships necessary to successfully bring their developed intellectual property (IP) to market. Final report will include system design, experimentation findings, and commercialization plan. 

PHASE III: Upon successful completion of Phase II, the contractor may be asked to demonstrate the full utility of the developed AI&ML augmented polarimetric imaging system to various DoD Program Managers (PMs) who have expressed interest in the developed technology. Phase III may include further modification and ruggedization depending on customer needs. Such evaluation will take place at an appropriate U.S. Army field-test facility. This will also include further maturation of the system in which reduction in size, weight and power (SWaP) will be examined. The candidate is expected to pursue civilian applications and additional commercialization opportunities, e.g., remote sensing of geological formations, enhanced surveillance for homeland/boarder security, and enhanced machine vision and inspection used in various manufacturing process. 

REFERENCES: 

1: K. Gurton, M. Felton, L. Pezzaniti, "Remote detection of buried land-mines and IEDs using LWIR polarimetric imaging", Optics Express, Vol. 20 Issue 20, pp.22344-22359 (2012).

2:  L. Pezzaniti, D. Chenault, K. Gurton, M. Felton, "Detection of obscured targets with IR polarimetric imaging", Proc. SPIE 9072, Detection and Sensing of Mines, Explosive Objects, and Obscured Targets XIX, 90721D, May 29, (2014).

3:  A. Yufa, K. Gurton, G. Videen, "Three-dimensional (3D) facial recognition using passive LWIR polarimetric imaging", Appl. Opt. vol. 53, no. 36, pp. 8514-8521, Dec. (2014).

4:  N. Short, S. Hu, P. Gurram, K. Gurton, A. Chan, "Improving cross-modal face recognition using polarimetric imaging", Optics Letters vol. 40, 6, pp. 882-885 (2015).

5:  R. Girshick, "Fast r-cnn", IEEE International Conference on Computer Vision (ICCV), December 7-13 (2015), Santiago, Chile.

6:  S. Hu, N. Short, K. Gurton, "Exploiting polarization-state information for cross-spectrum face recognition", 2015 IEEE 7th International Conference on Biometrics Theory, Applications and Systems (BTAS), September 8-11, (2015), Arlington, VA.

7:  J. Dai, H. Qi, Y. Xiong, Y. Li et al., "Deformable convolutional networks", IEEE International Conference on Computer Vision (ICCV), October 22-29 (2017), Venice, Italy.

8:  K. He, X. Zhang, S. Ren, and J. Sun, "Spatial pyramid pooling in deep convolutional neural networks for visual recognition", IEEE Trans. On Pattern Analysis and Machine Intelligence, 37(9), pp. 1904-1916, (2015).

9:  J. Tyo, D. Goldstein, D. Chenualt, J. Shaw, "Review of passive imaging polarimetry for remote sensing applications", Appl. Opt. vol. 45, no. 22, (2006).

10:  S. Hu, N. Short, K. Gurton P. Gurram, , C. Reale, "MWIR-to-Visible and LWIR-to-Visible Face Recognition Using Pa1rtial Least Squares and Dictionary Learning", Face Recognition Across the Electromagnetic Spectrum, Editor, T. Bourlai, Springer Press (2015).

11:  S. Shuowen, N. Short, K. Gurton, B. Riggan, "Polarimetric Thermal Based Face Recognition", Polarization, Measurement, Analysis, and Remote Sensing XII, SPIE Defense & Commercial Sensing Symposia, April 17-24, Baltimore, MD (2106).

KEYWORDS: Artificial Intelligence (AI), Machine Learning (ML), Thermal Imaging, Polarimetric Imaging, Anomaly Detection, Long-wave Infrared (LWIR), Mid-wave Infrared (MidIR) 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Develop an advanced acoustic particle velocity-pressure sensory system that is compact, ruggedized, and modular for anticipated missions involving acoustic localization, signal intelligence and other uses. 

DESCRIPTION: The U.S. Army is seeking research and development in acoustic particle velocity and acoustic pressure sensing technologies that can be implemented for use in acoustic signal detection, localization, tracking, and characterization. The technologies must be highly modular and capable of integration into atmospheric acoustic detection systems both current and future. Technologies focusing on modular design are highly desired. An environmentally self-aware system is envisioned. Current microphone array systems are used to detect, localize, and classify acoustic sources. Dependent upon the source and range of interest, these systems have large foot prints, ranging from several to tens of square meters. The Army seeks reduced Size, Weight, and Power (SWaP) systems. Systems that not only reduce the array system footprint, but also reduce power are highly desired. Versatility of usage is important, as sources of interest may be harmonic or impulsive, transient or continuous. Systems may be deployed in a variety of outdoor environments, to include, urban, desert, mountainous, and littoral. Ruggedized systems that can withstand environmental extremes are a necessity for outdoor emplacement. Systems may be land-based or airborne, on the move or stationary. 

PHASE I: The company will define and develop a concept for a compact acoustic particle velocity (three-dimensional)-pressure sensory system (APV-P) with modularity to include environmental state measurements (APV-P/E) that meets the requirements as stated in the topic description. The company will demonstrate the feasibility of the concept in meeting Army needs and will establish that the concept can be developed into a useful product. Material testing and analytical modeling will establish feasibility. The concept development effort should assess the importance of several acoustic sensing factors for the APV-P, such as dynamic range, wind noise mitigation, signal fidelity, preservation of waveform, sampling rates, well-defined calibration, and ease of calibration. Evidence of design optimization of these parameters, as well as a comparison between model predictions and measured performance are required. Modularity of the acoustic-environmental APV-P/E system, to include integrating meteorological sensors, should be established. Environmental parameters to be measured include wind velocity (speed and direction), humidity, temperature, and atmospheric pressure. Plans for implementing the APV-P will be included as an output of Phase I, along with estimated performance. The APV-P will be designed to operate at frequencies between 0.1 Hz to 10 kHz, but demonstration below 0.1 Hz is also desired. The minimum dynamic range of the APV-P should be -10 dB to 150 dB, though a larger range, on both sides, is desired. Methods to manage different sound levels should be considered, such as adjustable gains. Data acquisition should have a minimum sampling rate of 25 kHz, with a minimum of 24-bit resolution. Sensitivity of the particle velocity detection should be established to correspond with the sensitivity of the pressure sensing. Of particular concern is calibration of the system; methods for in-field, self-calibration are desired. Operational conditions also should be considered, the APV-P/E system should fully function between -30 to 70 degrees Celsius, though a larger performance range is desired. A ruggedized system is required, being able to operate in severe environments, including rain and fine-particulate environments. Environmental parameter sampling should provide for atmospheric (thermal-mechanical) turbulence characterization at the acoustic scales. 

PHASE II: Based on the results of Phase I, the company will develop a prototype APV-P/E for evaluation. The prototype will be evaluated to determine the capability in meeting performance goals and Army requirements. System performance will be demonstrated through prototype evaluation and modeling or analytical methods over the required range of parameters. Evaluation results will be used to refine the prototype into a design that will meet Army requirements. The APV-P system should include wind noise mitigation. Documentation should include analyses comparing system response to scientific grade microphones, performance for harmonic and impulsive sources, direction finding compared to conventional systems (including azimuth, elevation, and ranging sensitivity), assessment of wind noise mitigation, and preservation of acoustic waveform. 

PHASE III: The company will support the Army in transitioning the technology for Army field use. The company will develop an APV-P/E system according to the Phase III development plan for evaluation to determine its effectiveness in an operationally relevant environment. The company will support the Army for test and validation to certify and qualify the system for Army use and transition the APV-P/E to its intended platform. The envisioned military applications of the APV-P/E system include: detection, localization, tracking, and classification of a variety of sources, to include sniper and small-arms fire, rocket launches, explosions, and ground and airborne vehicles; characterization of atmospheric turbulence; and studies of acoustic wavefronts. A compact design is envisioned, allowing emplacement on ground and air vehicles. PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: The APV-P/E system has commercial applications that include gunshot detection and localization, aircraft/unmanned aircraft vehicles localization and tracking, intruder detection, environmental hazard assessments (e.g., volcanic and tornadic activity), and acoustic tomography of the atmosphere. The commercial market is typically quick to adopt technology that enhances performance while controlling cost and reducing SWaP. The company is expected to pursue civilian applications and additional commercialization opportunities. 

REFERENCES: 

1: L Solomon, L Sim, and J Wind, "Analysis of MEMS-based Acoustic Particle Velocity Sensor for Transient Localization," U.S. Army Research Laboratory Technical Report, ARL-TR-5686 (2011).

2:  SL Collier, et al, "Atmospheric turbulence effects on acoustic vector sensing," Proc. Meet. Acoust. 30, 045009 (2018).

3:  DC Swanson, Signal Processing for Intelligent Sensor Systems (Taylor & Francis, 2000).

4:  K Attenborough, KM Li, and K Horoshenkov, Predicting Outdoor Sound (CRC Press, 2006).

5:  R Raspet, et al, "New Systems for Wind Noise Reduction for Infrasonic Measurements," in Infrasound Monitoring for Atmospheric Studies: Challenges in Middle-atmosphere Dynamics and Societal Benefits. Second Edition. (Editors: A Le Pichon, E Blanc, A Hauchercorne

6:  Springer International Publishing, 2018).

KEYWORDS: Acoustic Pressure, Acoustic Particle Velocity, Microphone, Acoustic Vector Sensor, Self-aware Sensor 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Provide algorithms capable of compiling information from multiple frames acquired from a moving unmanned aerial vehicle. This algorithm will consolidate video data from an unnamed air vehicle in the form of data vectors that represent ground locations from multiple angles of observation. 

DESCRIPTION: U.S. Army RDECOM CERDEC Night Vision and Electronic Sensors Directorate is supporting protection of combat vehicles through detection of obstacles that threaten maneuverability in battlespace environments. We are developing sensors mounted on unmanned air vehicles to detect and localize landmines, natural or manmade topography, and surface obstacles that limit maneuverability or threaten the combat vehicle. To aid in this goal we will collect data over an environment from multiple look angles to improve our knowledge of the objects or conditions at ground locations. We believe that having multiple samples at a ground location will produce better features for subsequent algorithms. A necessary precondition of this process is to sort data from pixelated images of the video into vectors of data associated with particular ground locations, thus capturing a location’s data from multiple positions. We seek assistance in this area from qualified companies who can implement algorithms that will identify terrain features from multiple video frames collected by an airborne imaging system. Algorithms should process this data to determine 3D point clouds and subsequently assign to these points data associated with that location from multiple cameras and look angles. Topography and surface objects in the scene should be accounted for in the algorithms to appropriately register data to particular ground locations. The means of achieving this objective may include, but are not limited to, structure from motion, image transforms and photogrammetry. It is desirable that 3D information about the environment be obtained as an intermediate product. A potential benefit of this level of processing is the ability for the algorithm to discriminate above ground clutter from surface level terrain or obstacles. Likewise, information about the relative attitude of the air platform would be beneficial. Contractor data may be used to develop the algorithms, but as these algorithms mature Government provided data will be utilized to assess performance on data collected at Government test sites. The algorithm’s objective will be to accurately register image data to ground locations from multiple imaging systems mounted to the same platform. This algorithm will preferentially operate using image data alone. Inertial Measurement Unit (IMU), Global Position System (GPS), and height data may be brought to bear if significant improvements to output quality are achievable; however preference is given to methods that operate in GPS denied environments. Subsequent detection processing of the assembled feature vectors should be considered in the context of improving resolution and registration accuracy, but this solicitation is does not encompass advanced automatic target detection development. 

PHASE I: This effort should identify algorithms capable of registering image data to ground locations. Preliminary testing of contractor or modeled data should be performed to determine the ground sampling density achievable as a function of standoff distance, magnification and pixel size. The impact of optical distortions, frame rate, range of collection and nadir vs. slanting look angles should be characterized to guide future data collection activities. The final report will be include the expected performance as a function of system parameters and sufficient information to determine the necessary conditions for sensors and platforms to achieve accurate image registration to ground locations. 

PHASE II: This effort will implement the algorithm as software to produce 3D point clouds and associated image intensity data from Government data. Data assessment methods will be developed to determine the accuracy and stability of algorithm for various controlled data collections as well as field conditions without fiducial targets. The algorithm will show a path to continuous operation at realistic frame rates. The algorithm will be implementable on processing hardware scaled for size, weight, and power appropriate for an unmanned aerial vehicle. The algorithm should be demonstrated on such a processor or demonstrated to specify the processing and computation needs required. Resolution is desired on the order of 10cm for select regions of interest. Thus, the holistic algorithm may require trivial pre-screener processing to limit processing regions requiring improved resolution. The Phase II final report will include detailed system (software and hardware) design, system capability and limitations, detailed summary of testing and results, lessons learned, critical technology and performance risks. 

PHASE III: The Phase III goal is to develop and implement accurate image registration algorithms on processors for UAVs. This may be combined as a complete product for commercial sales, or as an algorithmic add on that utilizes Government or commercial sensors and platforms. This phase will improve accuracy of the methods and produce consistent feature vectors of image data associated with locations in the scene. 

REFERENCES: 

1: Irschara, Arnold, Christopher Zach, Jan-Michael Frahm, and Horst Bischof. "From structure-from-motion point clouds to fast location recognition." In Computer Vision and Pattern Recognition, 2009. CVPR 2009. IEEE Conference on, pp. 2599-2606. IEEE, 2009.

2:  Lingua, Andrea, Davide Marenchino, and Francesco Nex. "Performance analysis of the SIFT operator for automatic feature extraction and matching in photogrammetric applications." Sensors 9, no. 5 (2009): 3745-3766.

3:  Poelman, Conrad J., and Takeo Kanade. "A paraperspective factorization method for shape and motion recovery." IEEE transactions on pattern analysis and machine intelligence 19, no. 3 (1997): 206-218.

4:  Zhang, Junzhe, and G. Okin. "Quantifying vegetation distribution and structure using high resolution drone-based structure-from-motion photogrammetry." In AGU Fall Meeting Abstracts. 2017

KEYWORDS: Structure From Motion, Image Registration, Optical Flow, Unmanned Aerial Vehicle 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Develop and demonstrate techniques and algorithms for Deep Generative Modeling for the creation of Infrared (IR) datasets to facilitate Machine Learning and Aided Target Recognition (AiTR). 

DESCRIPTION: Applications of Deep Learning and Machine Learning to imagery and video have been dramatic in the last decade. However, these achievements have been almost entirely based on visible band imagery and video. The data requirements of these algorithms are enormous, and developers have been able to rely on masses of readily available visible band data. Militarily significant IR data does not currently exist in the quantities and varieties necessary to fully leverage the advantages of Deep Learning. What is needed a set of techniques and algorithms which can artificially generate militarily significant (as in specific localities and target types) IR video and imagery in entirety and to augment existing IR data with novel prescribed objects and targets. Success and promise has recently been shown by Generative Adversarial Networks. However, these image constructions are mostly intended for visual effect. Much higher fidelity is essential to training AiTRs. Also artificial IR modeling systems exist at Night Vision and Electronic Sensors Directorate (NVESD). This effort aims at overcoming data limitations listed above and enhancing realism of current NVESD modeling systems. The goal is to support an IR AiTR effective fieldable system—enhancing vehicle threat detection and avoidance. This effort directly supports Army Modernization Priority: Next Generation Combat Vehicle (NGCV)—benefitting the automation associated with the NGCV through improved algorithm performance. This effort will enable NGCV sensors to rapidly determine external threats and alleviate operator fatigue via automation of surveillance and navigational functions. 

PHASE I: Show proof of concept for Deep Generative Modeling algorithms for IR imagery and video synthesis. Show proof of concept for algorithms to greatly improve realism of synthetic imagery. Integrate algorithms into comprehensive algorithm suite. Test algorithms against existing NVESD modeling methodologies. Demonstrate feasibility of techniques in creating IR video sequences. Distribute demonstration code to Government for independent verification. Successful testing at the end of Phase 1 must show a level of algorithmic achievement such that potential Phase 2 development demands few fundamental breakthroughs but would be a natural continuation and development of Phase 1 activity. 

PHASE II: Complete primary algorithmic development. Complete implementation of algorithms. Test completed algorithms on government controlled data. System must achieve 25% improvement in classification rate and false alarm rate over AiTR algorithms trained on real imagery alone (using government baseline AiTR algorithm). Principle deliverables are the algorithms. Documented algorithms will be fully deliverable to government in order to demonstrate and further test system capability. Successful testing at end of Phase 2 must show level of algorithmic achievement such that potential Phase 3 algorithmic development demands no major breakthroughs but would be a natural continuation and development of Phase 2 activity. 

PHASE III: Complete final algorithmic development. Complete final software system implementation of algorithms. Test completed algorithms on government controlled data. System must achieve 25% improvement in classification rate and false alarm rate over algorithms trained on real imagery alone (using government baseline AiTR algorithm). Documented algorithms (along with system software) will be fully deliverable to government in order to demonstrate and further test system capability. Applications of the system will be in NVESD Multi-Function Display Program, vehicle navigation packages, and AiTR systems. Civilian applications will be in night surveillance, crowd monitoring, navigation aids, and devices requiring rapid adaptation to new environments. 

REFERENCES: 

1: Steven A. Israel

2:  J.H. Goldstein

3:  Jeffrey S. Klein

4:  James Talamonti

5:  Franklin Tanner

6:  Shane Zabel

7:  Philip A. Sallee

8:  Lisa McCoy, "Generative Adversarial Networks for Classification", 2017 IEEE Applied Imagery Pattern Recognition Workshop (AIPR).

9:  Dimitris Kastaniotis

10:  Ioanna Ntinou

11:  Dimitrios Tsourounis

12:  George Economou

13:  Spiros Fotopoulos, "Attention-Aware Generative Adversarial Networks (ATA-GANs)", 2018 IEEE 13th Image, Video, and Multidimensional Signal Processing Workshop (IVMSP).

14:  Parimala Kancharla

15:  Sumohana S. Channappayya, "Improving the Visual Quality of Generative Adversarial Network (GAN)-Generated Images Using the Multi-Scale Structural Similarity Index ", 2018 25th IEEE International Conference on Image Processing (ICIP).

KEYWORDS: Deep Learning, Generative Adversarial Networks, Aided Target Recognition, Neural Networks, Infrared Video 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Evaluate, develop and demonstrate the novel application of emerging commercial technologies for heterogeneous integration of infrared photodetector arrays and CMOS-based multiplexing circuitry. 

DESCRIPTION: The Army needs the highest performance infrared sensors for tactical and strategic overmatch. Mission-specific applications for high-sensitivity sensors extend across multiple infrared bands, including long wavelength (8-12 microns). These requirements have led to the development of infrared focal plane arrays (IRFPA) with large formats (~ megapixel) and small pixel pitch (~ 10 micron). Such IRFPAs consist of an array of photodetectors hybridized to a CMOS-based multiplexing circuit (ROIC), which reads out the photo-generated current to create useful imagery and information. ROIC design has evolved to improve sensor performance and to include more on-chip functionality, such as digitization and signal processing. Most current IRFPAs are fabricated using flip chip (C4), die-to-die bonding/interconnect processing. Technological developments in commercial, three-dimensional (3D), wafer-to-wafer level integration are leading to interconnect densities [1, 2, 3] relevant to state-of-the-art IRFPA applications. Such 3D integration offers potential, significant cost savings for IRFPA fabrication, particularly, if wafer-to-wafer integration can be realized. However, many technical challenges and uncertainties exist to such an implementation, including, but not limited to: limited thermal tolerance of typical infrared devices; wafer size mismatch between detector and ROIC; potential contamination/diffusion issues associated with interconnect materials (Cu, W, Sn etc.); compatibility with cryogenic operation, to include thermal cycling reliability. Non-technical challenges need also be considered such as: actual cost benefits, given the potential technical constraints, relatively small production quantities [4]; security, trustworthiness of hardware, foundry etc. [5]. The goals of this project are: to evaluate and analyze 3D integration technologies in the context of IRFPA hybrid assembly; to develop/modify a 3D integration process compatible with a relevant IRFPA product; to implement, demonstrate, test and evaluate, in hardware, application of 3D integration to a relevant IRFPA product. For the purposes of this project, an IRFPA product that is relevant to Army requirements is defined by the following characteristics: cryogenically operated; cut-off wavelength > 5 microns; format > 640 x 480 pixels; pixel pitch < 15 microns. 

PHASE I: The performer shall evaluate and analyze 3D integration technology in the context of IRFPA fabrication: i.e. detector array to ROIC hybridization. This analysis shall include technical, cost and security considerations. This analysis shall consist of a trade study of various processes and parameters constrained by compatibility with IRFPA processing and operation: for example, comparison of wafer-to-wafer, die-to-wafer and die-to-die integration modes. Based upon the results of this analysis, the performer shall develop a plan to develop, to implement and to demonstrate 3D integration technology in an IRFPA product that is relevant to Army requirements. 

PHASE II: The performer shall design and develop a 3D integration process that is compatible with a relevant IRFPA product based upon analysis and planning of Phase I. The performer shall implement, demonstrate, test and evaluate the resulting process, in hardware, in a relevant IRFPA product. 

PHASE III: The performer shall transition technology to appropriate foundries and/or industries for commercial implementation of resulting processes, products and/or intellectual property. Dual use applications include: machine vision, autonomous vehicles, security, process control, environmental monitoring, scientific instruments, and astronomy. 

REFERENCES: 

1: Wang, L, et al., "Direct Bond Interconnect (DBI®) For Fine-Pitch Bonding in 3D and 2.5D Integrated Circuits," 2017 Pan Pacific Microelectronics Symposium, 6-9 Feb. 2017.

2:  Gao, G. et al., "Scaling Package Interconnects Below 20μm Pitch with Hybrid Bonding," 2018 IEEE 68th Electronic Components and Technology Conference, pp. 314-322 [DOI: 10.1109/ECTC.2018.00055]

3:  Fournel, F., et al., "From Direct Bonding Mechanism to 3D Applications," 2018 IEEE International Interconnect Technology Conference (IITC), pp. 175-178, 4-7 Jun. 2018. [DOI: 10.1109/IITC.2018.8430293]

4:  Lujan, A., "Comparison of Package-on-Package Technologies Utilizing Flip Chip and Fan-Out Wafer Level Packaging," 2018 IEEE 68th Electronic Components and Technology Conference, pp. 2089-2094, [DOI 10.1109/ECTC.2018.00313]

5:  Knechtel, J., et al., "Large-Scale 3D Chips: Challenges and Solutions for Design Automation, Testing, and Trustworthy Integration," IPSJ Transactions on System LSI Design Methodology, vol. 10, pp. 45-62, Aug. 2017 [DOI: 10.2197/ipsjtsldm.10.45]

KEYWORDS: Infrared Focal Plane Array, IRFPA, 3D Integration, Heterogeneous Integration, Wafer Bonding, Direct Bonding, Interconnect, Hybridization, Flip Chip Bonding 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Develop and demonstrate a foveated headworn display that uses an eye tracker to determine eye location and provides high resolution to the display where the eye is pointed and lower resolution to other areas of the display for power, heat, and bandwidth reduction. 

DESCRIPTION: High resolution microdisplays are essential for providing the human interface to high resolution digital sensors and wide field of view augmented and mixed reality vision systems used for Soldier Lethality. Reduction of power, bandwidth, and head borne heat of these microdisplays is important for all DoD application, but it is especially important for untethered infantry. The resolution of the eye is very high in the area of the fovea, but it is greatly reduced in all other areas, so most of the resolution on a wide field of view large format microdisplay is not being used – only the part within the eye’s fovea is. A 2,048 x 2,048 reconfigurable microdisplay capable of reduced power operation with a moveable full-resolution window within a field of reduced resolution has been developed under government contract and is available as GFE for this effort, but an alternative display solution is also acceptable. Coupling a reconfigurable display with an eyepiece and an eye tracker would allow power to be saved by keeping the high resolution area of the display only where the fovea is located. This project would determine if a foveated display can provide sufficient performance compared to a 100% full resolution display while reducing power and bandwidth. The Offeror shall develop a foveated HMD demonstrator that includes an eye tracker to determine the eye pointing location and thereby keep the high resolution foveal display spot in synch with the user’s line of sight. 

PHASE I: Create a notional design for the demonstrator. Build a demonstrator that can be large scale (desktop display and computer) that shows eye tracking and reduces the resolution (electronically or optically) of the display in areas outside the fovea (TRL 4). 

PHASE II: Build demonstrator with an eye tracker and >1080p HMD (can use GFE Reconfigurable Display) that can be reconfigured with its own electronics or with software/hardware built by the Offeror that includes a reduction in power in the foveated mode vs. full resolution (TRL 5). The demonstrator will be used to examine the visual performance for detecting and responding to peripheral visual cues based on the interaction of the foveal area profile vs. the reduced display resolution threshold in the peripheral zone. The demonstrator will include a way to measure the power for full vs. reduced resolution. 

PHASE III: Implement the foveated display design into a military HMD, possibly partnering with a HMD manufacturer (TRL 6). Address integration issues, cost, and power reduction vs. design complexity. 

REFERENCES: 

1: Clarence E. Rash et al., Helmet-Mounted Displays: Sensation, Perception and Cognition Issues, ed. Clarence E. Rash, U.S. Army Aeromedical Research Laboratory (2009)

2:  Kyle R. Bryant, "Foveated Optics", SPIE Proceeding Volume 9822 Advanced Optics for Defense Applications: UV through LWIR (2016)

3:  Marcus Nystrom, Kenneth Homqvist, "Deriving and evaluating eye-tracking controlled volumes of interest for variable-resolution video compression", SPIE Journal of Electronic Imaging Vol 16, No 1 (2007)

KEYWORDS: Microdisplay, Foveated Display, Reconfigurable Display 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Develop and demonstrate a variable attenuator for head-worn see-through day/night displays suitable for military aviation and untethered infantry use. Attenuator will capable of changing from high optical transmission for an unobscured view of the environment to low transmission to enhance the contrast of the display versus the ambient. 

DESCRIPTION: See-through displays, which are used for situational awareness and targeting for Soldier Lethality and Future Vertical Lift, can be overwhelmed by high level ambient light such that the content of the display is not readable. A contrast of 1.2:1 of the display to the background is the general rule for see-through readability, with the worst case ambient conditions being 2,000-fL for a white cloud or snow bank on a clear day. Reducing the transmission of the see-through optic, such as a visor, can aid with display contrast and readability, but the transmission needs to be high in some operations, especially at night, to allow the user to see details in the real environment through the optic. Arbitrarily driving the brightness of the display source brighter would enable readability, but it may increase power and thermal management demands beyond allowable limits, especially for untethered infantry. It also limits the display and optical technologies available for augmented reality solutions. See-through displays are also subject to external hazards and threats that occluded systems are not. A continuously variable attenuator can allow full daylight readability in bright ambient conditions, a clear view of the real world in night operations, and can have built in protections against hazards and threats. One potential form of the variable attenuator will be to provide the ability to transition bi-directionally between a broad-band, visually neutral, low transmission state of not more than 20% and a broadband, optically neutral, high transmission state of at least 80% in under 1 second. Other potential variable attenuator implementations for consideration include video rate attenuation switching speeds, localized and/or tailorable spectral attenuation/switching, and integrated eye/display hazard and threat protection. This effort will include the development of the 80%/20% ambient transmission attenuator and will also include its integration into a headworn system. An automatic adjustment of the transmission is optional, but a manual adjustment override is essential. Hazard and threat protection is also optional. 

PHASE I: Complete a notional design and model performance for a variable attenuator for day/night readability. Address spectrum, level of attenuation, switching speeds, localized attenuation, and potential hazard and threat protection. Provide sample demonstrators of attenuator technology (TRL 4). Phase I demonstrators may utilize planar substrates. 

PHASE II: Refine system design and build lab demonstrator capable of a minimum of 80%/20% continuous variability (spectrally flat) and will include other design concepts Offeror intends to include, such as localized attenuation (TRL 5). Develop a fully functional demonstrator that is integrated with a see-through head worn display (TRL 6). This demonstrator will examine the commercial practicality and cost related to implementing the variable attenuator on curved and/or plastic substrates. 

PHASE III: Integrate with a military AR HMD, possibly partnering with an HMD manufacturer for this effort (TRL 7). Apply technology to larger HUDs in aircraft and to vehicle windows. Implement hazard and threat protection if not already included. 

REFERENCES: 

1: Clarence E. Rash et al., Helmet-Mounted Displays: Sensation, Perception and Cognition Issues, ed. Clarence E. Rash, U.S. Army Aeromedical Research Laboratory (2009)

2:  Russell S. Draper et al., "Electrochromic Variable Transmission Optical Combiner", SPIE Proceedings Volume 5801, Cockpit and Future Displays for Defense and Security (2005)

3:  Thomas H. Harding, Clarence E. Rash, "Daylight luminance requirements for full-color, see-through helmet-mounted display systems", SPIE Optical Engineering Vol. 56 Issue 5 (2017)

4:  Thomas H. Harding et al., "HMD daylight symbology: color choice and luminance considerations", SPIE Proceedings 10197, Degraded Environments: Sensing, Processing, and Display (2017)

KEYWORDS: Attenuator, Optical Attenuator, Variable Attenuator, See-through Display, Augmented Reality, HMD, HUD 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Exploration of advanced concepts for high-performance, low-cost, uncooled infrared detectors and focal plane arrays for soldier systems 

DESCRIPTION: Exploitation of recent advances in electronics, optoelectronics, communications, and quantum computing may provide future breakthroughs in infrared detectors, offering promising opportunity for soldier-worn sensors. Examples of these advances include colloidal semiconductor quantum dots, quantum wire carbon nanotubes, and graphene with combined structures that could potentially enable highly beneficial detector designs for photoconductors, photodiodes, or field effect transistors (1-3). These and similar technologies may be the future steps for high-speed, compact, lightweight, and low-cost sensor operation. In this topic, high-speed, high-performance infrared detector concepts operating at room temperature are being pursued to support small, lightweight, low-power soldier sensor systems that perform better than current imagers. Detectors should operate at very high speeds like quantum detectors, and at room-temperature like bolometers. For the future Army dismounted soldiers, low cost and small size, weight and power (SWaP) infrared sensors are critical to equip our soldiers in the battlefield. This topic has significant impact on the CFTs Soldier Lethality, as well as Future Vertical Lift and Next Gen Combat Vehicles. The detailed detector performance includes but is not limited to 1) High speed at 120Hz operation, 2) High performance comparable to or better than the current bolometers at room temperature, 3) Suitability for large format, small pitch focal plane array fabrication, 4) Compatibility with existing readout integrated circuitry for detector integration, and 5) Cost lower than current bolometers. Detectors should operate at room temperature with a D* of ~1E10 Jones and response time in the millisecond range. The cutoff wavelength can be in the long- or mid-wavelength infrared spectrum. It is highly desired to have the capability to capture a thermal image without light. Low-light-level, visible or near infrared detectors will also be considered. A suitable digital readout integrated circuit (ROIC) should be identified for uncooled detector use. 

PHASE I: In Phase I, an innovative detector concept should be modeled and designed and detectors should be grown and processed to demonstrate single element diodes. 

PHASE II: The innovative concept should be demonstrated at the infrared focal plane array (FPA) level with frame rate at >120Hz and performance similar to current bolometers at room temperatures. 

PHASE III: Develop and execute a plan to market and manufacture the new focal plane arrays (FPAs). Assist Army in transitioning this technology to the appropriate Prime Contractor(s) for the engineering integration and testing. The contractor shall pursue commercialization of the various technologies and electro-optic/infrared (EO/IR) components developed in Phase II for potential commercial uses in such diverse fields as law enforcement, rescue and recovery operations, environmental monitoring sensors, maritime and aviation collision avoidance sensors, medical test equipment, homeland defense surveillance, and other infrared detection and imaging applications. 

REFERENCES: 

1: "MWIR Imaging With Low Cost Colloidal Quantum Dot Films", Christopher Buurmaa, Richard E. Pimpinellaa, Anthony J. Ciania, Jered S Feldmana, Christoph H. Greina, and Philippe Guyot-Sionnestb, Proc. of SPIE Vol. 9933 993303-3 (2017)

2:  "Broadband Photodetectors Enabled by Localized Surface Plasmonic Resonance in Doped Iron Pyrite Nanocrystals", Maogang Gong,* Ridwan Sakidja, Qingfeng Liu, Ryan Goul, Dan Ewing, Matthew Casper, Alex Stramel, Alan Elliot, and Judy Z. Wu*, Adv. Optical Mater. 6, 1701241, (2018).

3:  "Room temperature performance of mid-wavelength infrared InAsSb nBn detectors", Alexander Soibel, Cory J. Hill, Sam A. Keo, Linda Hoglund, Robert Rosenberg, Robert Kowalczyk, Arezou Khoshakhlagh, Anita Fisher, David Z.-Y. Ting, and Sarath D. Gunapala, Applied Physics Letters 105, 023512 (2014).

KEYWORDS: Uncooled Infrared Detectors, Focal Plane Arrays, Quantum Detectors 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: Develop a specific cost-effective point-of-care assay to rapidly identify dengue exposure history in the warfighter enabling force protection readiness and high-throughput mass dengue vaccination programs 

DESCRIPTION: Dengue virus (DENV) is a growing threat to tropical regions and the warfighter. It is a leading cause of fever in military deployed to tropical regions [Gibbons, EID, 2012], and the global incidence of dengue has dramatically increased in the last three decades [Messina, Trends Microbiol, 2014]. DENV infections may lead to loss of operational readiness and maybe life threatening and difficult to manage in austere settings [WHO, https://www.ncbi.nlm.nih.gov/books/NBK143157/, 2009]. The four dengue virus serotypes complicate risk management and readiness. First dengue infections are often asymptomatic and dramatically increase the chance of a more severe infection when exposed to a second dengue serotype [Soo, PLOS One, 2011]. Clinical trials have shown that dengue vaccines are less effective and potentially dangerous when administered to those who have not been previously exposed to dengue, as is the case with the majority of the US Military [Sridhar, NEJM, 2018; Gibbons, EID, 2012]. The World Health Organization now recommends that determining dengue exposure history (serostatus) is critical to inform what vaccine strategy should be used in order to maximize dengue protection and avoid vaccine related harm [Vannice, Vaccine, 2018]. Immunological assays which can detect prior exposure to dengue do exist, but they are not point-of-care [Welch, J Virol Methods, 2014]. Moreover, standard immunoassays such as ELISA lack specificity to DENV as they cross-react to other flaviviruses, particularly Zika virus (ZIKV), and may cross react with Yellow-Fever and Japanese Encephalitis vaccine-derived antibodies [Priyamvada, PNAS, 2016]. The current, approved, gold-standard to accurately determine dengue exposure history is to use plaque-reduction neutralizing assays (PRNT). However, PRNTs are cumbersome, require a specimen send-out to a central reference laboratory, have low reliability between laboratories, and are costly [Rainwater-Lovett, BMC ID, 2012]. The turn-around time for a PRNT result is too long when large-scale dengue vaccine programs are underway, particularly for time-sensitive mass deployments. Waiting for PRNT results would be unfeasible even for routine recruit basic training vaccination programs. A more specific ELISA assay has been recently developed, but this is non-FDA approved and there is limited, if any, clinical experience with its use [Balmaseda, PNAS, 2017]. This assay was designed primarily as a clinical ZIKV diagnostic assay. Moreover, this assay is not point-of-care and requires laboratory expertise for use and interpretation [Balmaseda, PNAS, 2017]. Other point-of-care diagnostic assays for dengue are designed to detect acute infections, not prior dengue exposure [Zainah, J Virol Methods, 2009] A rapid, point-of-care assay which measures dengue exposures of recruits would allow immediate determination of whether a warfighter can be vaccinated for dengue, and/or whether the warfighter requires a different dengue vaccine product or schedule. This would be vital for time-sensitive dengue vaccination programs of large volumes of troops before deployment when it would not be possible to obtain their serostatus in a feasible time frame. It would also remove the need to perform thousands to millions of expensive, time-demanding PRNT assays in existing Department of Defense laboratories which currently do not have the capacity to perform such a large volume of reference dengue diagnostic tests. A point of care dengue specific exposure device will reduce risk of any current or future dengue vaccine and pre-deployment dengue exposure testing will identify soldiers and general population that are at increased risk of severe disease when traveling or deploying to high risk dengue regions of the world. Of note this device would not be an acute disease diagnostic to identify pathogens causing fever and dengue disease. While current acute point-of-care febrile disease diagnostic platforms can estimate primary versus secondary dengue infection, they are calibrated and validated to do so only during an acute febrile illness and they cannot accurately detect prior dengue exposure in the asymptomatic host which would typically have far lower circulating levels of anti-flavivirus antibodies. 

PHASE I: By the end of Phase I the successful applicant will have: (i) Conceptualized the assay to include potential targets of dengue verse other related flavivirus specificity and demonstrate with design and data package supporting claims of specificity. (ii) Conceptualized and defined the target assay characteristics including a) biospecimen type (e.g. blood, sera), biospecimen volume required and proposed route of access (e.g. fingerstick, 1mL of sera derived from venipuncture); b) analyte of interest (e.g. antibody class) and method of detection; c) envisaged assay read out (e.g. colorimetric, digital); d) anticipated field operating characteristics including assay thermostability, cold chain requirements, necessary reagents, and operator skill required to perform and interpret the assay; and e) crude cost estimate for each assay unit (iii) Developed technological milestones for the full development of this assay (iv) Outlined a set of performance goals for the validation of this assay, including in-vitro validations and subsequent clinical validations (iv) Explicitly described the target protein(s), antigen(s) or antibody(s) or other analytical target, including their reproducible functional and structural characteristics While the awardee is expected to select an appropriate target analyte, they are strongly encouraged to co-ordinate the choice of antigen/antibody with the COR Specifically, the awardee will have: • Performed the assay in a research laboratory setting and demonstrated that it can be performed without any laboratory infrastructure (i.e., demonstrated the feasibility of point-of-care use). • Performed the assay in a research laboratory setting and demonstrated the feasibility of using only a relatively small amount of biospecimen which would be readily available in a point-of-care setting (using a small amount of biospecimen) to detect the analyte. • Evaluated the prototype product on a pilot panel of flavi-virus exposed and unexposed biological specimens available through the COR 

PHASE II: The Phase II deliverables will include: (i) Construction and demonstration of the operation of the assay prototype (ii) A detailed plan for clinical validation (iii) Performance of a clinical validation of the assay on archived or prospectively collected bio-specimens from humans and higher order animals with known exposure to DENV, ZIKV, other flaviviruses and flavivirus vaccines already determined by gold-standard methods. This validation will include metrics of assay validity and reliability, with estimates of uncertainty around these metrics. This validation must address the broad genetic and antigenic diversity of DENV by global location. The expected performance parameters would be a sensitivity greater than 90% and a specificity greater than 90%, although the target performance characteristics may depend on the setting of use (see Phase III) and the pre-test probability of disease exposure and can be coordinated and refined with the COR. 

PHASE III: The expected Phase III end-state is an FDA approved, low-cost, point-of-care, closed-system, easy-to-use and easy-to-interpret assay which can be used on a relatively low volume of easily accessible biospecimen. The transfer from research to operational capacity would occur via the biotechnological industry pathway, such that appropriate scale up and feasible unit costs can be accommodated. This end-product would likely be used in vaccination clinics during basic recruit training and/or in vaccination clinics as part of large-scale pre-deployment soldier readiness programs. It is envisaged that this point-of-care test that could be operated by a nurse or other healthcare professional in the office without the need for laboratory expertise. The specific indication would to immediately determine a soldier’s dengue serostatus, permitting an on-the-spot decision about which vaccine product/schedule they need to receive (including a decision whether it is safe for the soldier to receive any dengue vaccine at all). A similar consumer group may be civilians presenting to a travel clinic for pre-travel dengue risk advice and vaccination. This end-product would also be critical for civilian population dengue vaccination programs and we would envisage it would be used on a population scale in dengue endemic regions to facilitate widespread dengue vaccination programs which are projected to greatly reduce the overall burden of dengue in many tropical regions, but which are currently restricted by host serostatus safety concerns. Current guidance from the WHO for the current single licensed dengue vaccine (which is now licensed in over 20 countries) is that the host dengue sero-status should be determined before vaccination [Vannice, Vaccine, 2018]. However, this may be logistically and financially prohibitive in many lower-resource regions, even if recently developed ELISA platforms are extensively validated and approved for diagnostic use [Turner, Trans R Soc Trop Med Hyg. 2018]. This envisaged product would therefore ‘unlock’ the full potential of currently licensed, and perhaps future dengue vaccines, to substantially reduce the burden of this disease. 

REFERENCES: 

1: Balmaseda A, Stettler K, Medialdea-Carrera R, Collado D et al. Antibody-based assay discriminates Zika virus infection from other flaviviruses. Proc Natl Acad Sci U S A. 2017 Aug 1

2: 114(31):8384-8389. doi: 10.1073/pnas.1704984114. Epub 2017 Jul 17.

3:  Gibbons RV, Streitz M, Babina T, Fried JR. Dengue and US military operations from the Spanish-American War through today. Emerging infectious diseases. 2012

4: 18(4):623-30

5:  Priyamvada L, et al. Human antibody responses after dengue virus infection are highly cross-reactive to Zika virus. Proc Natl Acad Sci USA. 2016

6: 113:7852–7857

7:  Sridhar S, Luedtke A, Langevin E, Zhu M, Bonaparte M, Machabert T, Savarino S, Zambrano B, Moureau A, Khromava A, Moodie Z, Westling T, Mascareñas C, Frago C, Cortés M, Chansinghakul D, Noriega F, Bouckenooghe A, Chen J, Ng SP, Gilbert PB, Gurunathan S, DiazGranados CA. Effect of Dengue Serostatus on Dengue Vaccine Safety and Efficacy. N Engl J Med. 2018 Jul 26

8: 379(4):327-340

9:  Vannice KS, Wilder-Smith A, Barrett ADT, Carrijo K, Cavaleri M, de Silva A, Durbin AP, Endy T, Harris E, Innis BL, Katzelnick LC, Smith PG, Sun W, Thomas SJ, Hombach J. Clinical development and regulatory points for consideration for second-generation live attenuated dengue vaccines. Vaccine. 2018 Jun 7

10: 36(24):3411-3417

KEYWORDS: Dengue Virus, Flaviviruses, Zika Virus, Dengue Vaccines, Diagnostic Assay, Immunoassay, Serostatus, Soldier Lethality 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Apply Machine Learning/Artificial Intelligence to target recognition algorithms in gun launched munitions. 

DESCRIPTION: The Army requires advancement in Autonomous Target Recognition (ATR) algorithms for seekers in gun launched applications. Currently, seekers are capable of target detection in low clutter environments. To field a fully effective weapon that is also safe for use in conditions where there is high fratricide or collateral damage concern, the ability to discriminate between target types and between friend and foe rapidly (within minutes) and under extremely dynamic conditions is required. This topic will apply advanced and innovative machine learning and/or artificial intelligence to current and future target sensor packages that will be used in artillery, tank and mortar munitions among others. This includes but is not limited to new algorithmic approaches and/or sensor fusion approaches to improve ATR capability at extended slant ranges (3-7km), and while searching large Field of Views (FOV) (up to 3000m radius). The ability to conduct ATR in relatively inexpensive (<$10K unit at 1000 units/year) seeker architectures is critical. The munitions will experience high shock (up to 45,000 g’s) throughout a range of temperature extremes (- 25 to +145 degrees F operating range). The algorithms shall be capable of operating on emerging commercial GPU products suitable to 155mm artillery SWaP-C constraints. Detailed requirements will be provided after contract award. 

PHASE I: Phase I will consist of development of prototype algorithms on representative hardware demonstrated in laboratory simulated environments. A final report will document testing results and present the top level plan to continue development in Phase II. 

PHASE II: Phase II will continue the success of Phase I and integrate the hardware/firmware solution into a representative gun fired munition and tested at a government test range to demonstrate the ability to discern multiple disparate targets within the timing required in multiple environmental conditions. The result of Phase II will be a prototype design, including applicable technical data, which will be integrated into current and future munition designs for advanced target recognition. 

PHASE III: Upon success of Phase II, these technologies would be transitioned to munitions currently in development. Commercial applications could include law enforcement, boarder patrol/control, wildlife tracking or any other application requiring aerial identification of specific items on the ground. 

REFERENCES: 

1: CONVOLUTIONAL NEURAL NETWORKS AS FEATURE EXTRACTORS FOR DATA-SCARCEVISUALSEARCHES, Hichem ben Abdallah, September 2016. http://www.dtic.mil/dtic/tr/fulltext/u2/1029659.pdf

2:  A large-scale controlled object dataset to investigate deep learning, Ali Borji, Saeed Izadi, Laurent Itti. http://www.dtic.mil/dtic/tr/fulltext/u2/1019864.pdf

3:  PROCEEDINGS OF THE GOVERNMENT NEURAL NETWORK APPLICATIONS WORKSHOP, 24-26 August 1992, http://www.dtic.mil/dtic/tr/fulltext/u2/a259638.pdf

4:  computer vision algorithms based on biological, mathematical, and computational principles that are relevant to automatic target recognition, Steven W. Zucker, November 2004. http://www.dtic.mil/dtic/tr/fulltext/u2/a435709.pdf

KEYWORDS: Machine Learning, Artificial Intelligence, Algorithm, Munitions, Ammunition, Extended Range, Artillery, Mortars, Precision, Target Recognition, Target Tracking 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Apply Machine Learning/Artificial Intelligence to aid in interpretation of radiography inspection results during non-destructive testing. 

DESCRIPTION: The Army relies on radiography inspection (e.g. x-ray and neutron) for non-destructive testing of munitions during production and special investigations. Interpreting the visual results of the inspections is a challenge and requires highly trained individuals (Level III Radiographers) to determine what, if any, problems actually exist. This topic will apply advanced and innovative machine learning and/or artificial intelligence to current and future non-destructive radiography inspection methods that use electronic imaging to identify defects and aid the operator in proper and timely interpretation of the results. As this technology is meant to be incorporated in a production line, the expectation is that it will support three dimensional inspection and interpretation of defects at a production rate of up to 1 unit per minute, and items up to 6.5 inches in diameter. Defects include cavities, porosity, piping, voids, gaps, low density, annular rings, cracks and inclusions ranging from 0.002" to 0.020". The technology must reside on a standard computer system linked to the inspection equipment and receive the electronic images from the radiography system. Specific interface requirements will be provided after contract award. This topic will also develop and deliver the output screens that provide the proper data and information that a Level II radiographer is trained to understand. 

PHASE I: Phase I will consist of development of prototype algorithms on representative hardware (to be defined prior to contract award)demonstrated in laboratory simulated environments. The government may also provide actual images obtained during prior government testing. A final report will document testing results and present the top level plan to continue development in Phase II. 

PHASE II: Phase II will continue the success of Phase I and integrate the hardware/software/firmware solution into a representative radiography system at a government facility (to be defined prior to Phase II contract award). The result of Phase II will be a prototype design, including applicable technical data, which will be integrated into current and future radiography inspection systems at multiple government locations. 

PHASE III: Upon success of Phase II, these technologies would be qualified and transitioned to inspection equipment at multiple government ammunition production and R&D facilities. Commercial applications could include medical imaging and inspection of high value and/or safety critical items. 

REFERENCES: 

1: "Automated Defect Recognition and Identification in Digital Radiography", P. Baniukiewicz, Journal of Nondestructive Evaluation, September 2014, Volume 33, Issue 3, pp 327–334 https://www.semanticscholar.org/paper/Artificial-Neural-Networks-and-Fuzzy-Logic-in-Sikora-Baniukiewicz/ee0271ebf15a2c2724700aea2372942c8415b037

2:  " Automatic Detection of Welding Defects using Deep Neural Network," Wenhui Hou et al, 2018 J. Phys.: Conf. Ser. 933 012006. http://iopscience.iop.org/article/10.1088/1742-6596/933/1/012006

3:  "Automatic Defect Recognition in X-Ray Testing Using Computer Vision," D. Mery and C. Arteta, 2017 IEEE Winter Conference on Applications of Computer Vision (WACV), Santa Rosa, CA, 2017, pp. 1026-1035. https://ieeexplore.ieee.org/document/7926702

4:  "Multiclass classification of weld defects in radiographic images based on support vector machines", Mekhalfa Faiza, and Nafaa Nacereddine. Signal-Image Technology and Internet-Based Systems (SITIS), 2014 Tenth International Conference on. IEEE, 2014. https://ieeexplore.ieee.org/document/7081517

5:  "Intelligent Segmentation Of Industrial Radiographic Images Using Neural Networks", Lawson, Shaun & Parker, Graham, Proceedings of SPIE - The International Society for Optical Engineering. 10.1117/12.188736, 1994. https://www.spiedigitallibrary.org/conference-proceedings-of-spie/2347/0000/Intelligent-segmentation-of-industrial-radiographic-images-using-neural-networks/10.1117/12.188736.full?SSO=1

6:  - NAS410 NAS Certification & Qualification of Nondestructive Test Personnel

KEYWORDS: Non-destructive Test, Radiography, X-ray, N-ray, Munitions, Testing, Machine Learning, Artificial Intelligence, Inspection 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: The Software Communications Architecture (SCA) v4.1 is an open architecture framework that defines a standard way to instantiate, configure, and manage waveform applications running on a radio hardware platform. The SCA decouples waveform software from its platform-specific software and hardware, facilitates waveform software re-use, and minimizes development expenditures. The SCA v4.1 specification increases cybersecurity, improves performance, enhances software portability, and affords opportunities to reduce development costs of SCA compliant products. DoD Instruction 8310.01, IT Standards in the DoD, 2 Feb 2015, states that program managers and developers will use IT standards in the DISR for IT system development, acquisition, and procurement to promote interoperability, information sharing, reuse, portability, and information security. The main objective is to develop an automated testing platform as a dynamic testing method for the SCA 4.1 compliance requirements that necessitate the execution of the waveform under test on a SCA 4.1 Test Platform. This effort develops an extensible environment for the construction, organization, execution, and summary of automated, reproducible compliance tests on SCA 4.1 waveform products. The JTNC Test & Evaluation Laboratory (JTEL) is the designated Test Authority of the SCA specifications compliance for the DoD and Commercial radios and waveforms. 

DESCRIPTION: The desired solution will provide an automated test platform for Tactical Communications Waveforms and Applications against the SCA v4.1 specification with the following features: • Modular and object oriented architecture that allows separation of test description from the test execution. • Implementation in C++ or Java without 3rd-party library dependence. • Able to execute on both Windows and Linux platforms • Able to read test configuration in eXtensive Markup Language (XML) • Scriptable and GUI-configurable execution models • Output comprehensive test reports in common formats (XML, CSV, HTML, and ASCII text) • User manual and Software Design Description (SDD) Solution should be deployable on a Windows or Linux platform and connection to a tactical radio set via USB cable and/or Ethernet cable. The resultant product of this effort would be transitioned to the Joint Tactical Network Center. Commercial application of this technology could include usage by vendor SDR developers whose desire is to test their waveforms’ compliance to SCA v4.1 specification. 

PHASE I: The Phase One deliverable will be a prototype and product documentation describing: • A Set of SCA v4.1 requirements that will be used in Phase 1 • Analysis of test approaches (dynamic and/or static) for the SCA v4.1 requirements • Design and implementation of a simple GUI to allow users to select a set of SCAv4.1 requirements for testing • Demonstrate a simple Application/Waveform test case • Provide test results in a test report in common formats (XML, CSV, HTML, and ASCII text) showing the Application/Waveform component under test, applicable SCA v4.1 requirements, results of the test, and set of metrics (number passed vs failed). • Document User Manual and Software Design Description 

PHASE II: Phase II will provide an automated compliance test solution for SCA 4.1 requirements that are applicable to SDR Applications/Waveforms. The tool employs both dynamic and static testing approaches since some of the SCA requirements may not be verified by dynamic testing. Phase II will provide an automated compliance test solution for SCA 4.1 requirements that are applicable to SDR Applications/Waveforms. The tool employs both dynamic and static testing approaches since some of the SCA requirements may not be verified by dynamic testing. Phase Two deliverables will include: • Provide a complete set of SCA v4.1 requirements that are developed in Phase II • Analysis of test approaches (dynamic and/or static) for the SCA v4.1 requirements • Design and implementation of GUI to allow users to configure the test cases and SCAv4.1 requirements. • Develop and demonstrate automated test tool for the SCA v4.1 requirements. • The test tool has reached the DoD Technical Readiness Level 6 at the end of Phase II. • Test report provides Waveform/Application components, applicable SCAv4.1 requirements, test results, and metrics • Product documentation includes User Manual and Software Design Description • Monthly technical discussions with TPOC and stakeholders • Quarterly Progress reports including all technical challenges, technical risk, and progress against the schedule. 

PHASE III: Phase III will integrate the tool developed in Phase II with the SCAv4.1 Test Suite (STS) that is developed by the JTNC Test and Evaluation Laboratory. The STS tool verify tactical radios against the SCA v4.1 specification. • Phase Three deliverables will include: o Prototype solution suitable for supporting PM TR or any programs that sponsor or develop Tactical radios or application/waveforms o Demonstration of the test tool with Tactical Communications Waveforms/Applications o Complete Source code of the tool o Test report in common formats (XML, CSV, HTML) o Product documentation includes User Manual and SDD o Quarterly Progress reports. The reports will include all technical challenges, technical risk, and progress against the schedule. 

REFERENCES: 

1: Joint Tactical Network Center, Software Communications Architecture Specification, Version 4.1, 20 August 2006

2:  Joint Tactical Network Center, Software Communications Architecture Specification Version 4.1 Features and Benefits, Version 1.0, 18 January 2018

3:  Syckle, F. V (6 March 2018), SCA v4.1 entered into the DoD Information Technology Standards Registry, https://www.army.mil/article/201618/sca_v41_entered_into_the_dod_information_technology_standards_registry

4:  Wireless Innovation Forum, SCA v4.1 Requirements Allocation, Objectives, and Verification Criteria, Version WINNF-16-P-0025-V1.0.0, 17 March 2017

KEYWORDS: Software Define Radio (SDR), Software Communications Architecture (SCA), Tactical Radios, Tactical Waveforms, Tactical Applications, Tactical Radio Services, Automated Test Tool 

TECHNOLOGY AREA(S): Ground Sea 

OBJECTIVE: An advanced, intelligent Lithium-ion 6T manufacturing end-of-line tester and cell selector system to improve 6T battery quality & performance. 

DESCRIPTION: The 28-V Lithium-ion 6T drop-in replacement battery (Li-ion 6T) is a critical technology to enhance energy storage to improve warfighting performance across the Army, Marines, and Navy. The Li-ion 6T is a drop-in replacement for legacy Lead-Acid 6T batteries for starting, lighting, and ignition (SLI) and silent-watch applications, and provides the same form, fit, and expanded function, including increased silent watch time, significantly extended cycle life, and faster recharge time. Deficiencies in Li-ion 6T manufacturing inspection technologies and processes could result in three possible undesirable outcomes: (1) battery products with latent defects, in either the cells or BMS, which causes premature failure or safety issues in the field (such as an internal cell short); (2) battery products with deficient performance for their intended function as a result of poorly matched cells (such as poor cycle life); or (3) low yield resulting in increased production cost through waste. While manufacturing technologies exist for basic cell selection and end-of-line testing, these processes could benefit substantially from innovations in cell analysis techniques, hardware-in-the loop modeling & simulation, and machine learning. Technologies developed should be specifically for Li-ion battery pack production processes versus cell production processes and should be specifically focused on cell selection at the start of the pack production process and end-of-line testing of the final product at the end of the pack production process. A Li-ion 6T battery product’s performance is directly affected by the cells chosen for the battery. Currently, cells within the Li-ion 6T battery are matched in many cases simply by capacity and internal resistance and manufacturing cell selection equipment and processes are not designed specifically with Li-ion 6T in mind. Accordingly, innovative solutions must be developed and demonstrated which will allow for enhanced cell selection & sorting as well as for Li-ion 6T battery pack end-of-line testing, designed to ensure that the military-specific SLI and silent-watch missions can be met by the final 6T product. Cell selection solutions should take into account technologies such as internal resistance measurement, internal short detection, electro-impedance spectroscopy, calorimetry, and neural networks as well as other innovative analysis techniques. Cell selection and pack end-of-line test technologies shall be capable of integration into a high-volume 6T production process of at least 500 packs/month, and should be scalable to processes of up to 2000 packs/month. End-of-line test solutions must be able to account for the whole operational voltage and temperature range of the battery as well as be capable of simulating pulse events such as cold crank. The systems and solutions developed should be open-architecture to the greatest extent possible. Solutions developed should include real-time modeling & simulation to allow for analysis of the suitability of a produced battery to meet Army requirements, such as Silent Watch. Technology developed should be generally applicable and adaptable to all Li-ion 6T products as well as to all low-voltage commercial Li-ion battery packs. Innovative solutions developed for pack end-of-line testing shall include the ability to determine compliance to all MIL-PRF-32565 periodic production inspection (PPI) tests and have a secure way of reporting results of PPI testing to the Qualifying Activity (such as public-private key encryption). The solutions should also be capable of learning in an effort to help reduce future failures through correlation of PPI/end-of-line test data to cell selection, with the goal of preventing batteries that fail compliance from making it into the field. 

PHASE I: Identify and determine the engineering, technology, and hardware and software needed to develop this concept. End-of-line test technologies developed shall include all listed PPI testing in Table VII of the MIL-PRF-32565, including: Physical characteristics, Dimensions and weights, Terminal posts and threaded sockets, Full charge capacity, Cranking amps, Charging, Charge acceptance, Safety protections, Workmanship, and Defects. Additionally, technologies developed should allow for prediction and assessment of whether the following IPI tests will be met by the battery including: Deep cycle life, High temperature deep cycle life, Retention of charge, Battery storage life, Battery service life, Surges, spikes, and starting operation, Voltage surges, Voltage spikes, and Electromagnetic compatibility/interference. Battery Management System Hardware in the Loop Simulation to determine BMS quality and compliance should also be considered to verify CAN bus requirements, “Measured parameters” tolerances, state of charge estimation accuracy, state of health estimation accuracy, and power capability estimation accuracy. Solutions developed shall improve yield and reduce waste, and consequently improve production costs, by at least 5%. Automated PPI testing using technologies developed under this effort shall reduce the time required for completion of PPI by half. Drawings showing realistic designs based on engineering studies are expected deliverables. Additionally, modeling and simulation (M&S) tools needed to drive the end-of-line tester and cell selection technology is expected. A bill of materials and volume part costs for the Phase I designs should also be developed. This phase also needs to address the challenges identified in the above description. 

PHASE II: Develop and integrate prototype hardware and software into high-volume manufacturing equipment using the designs and technologies developed in Phase I. Deliverables shall include electrical drawings and technical specifications, software, M&S and test results, and at least one Li-ion 6T pack end-of-line tester and one cell selector capable of integration into a high-volume Li-ion 6T manufacturing process and production line. The end-of-line tester and cell selector shall be designed initially for processing only one type/size of Li-ion 6T cell and Li-ion 6T pack product, but the technology shall be designed such that it is generally applicable to all Li-ion 6T cells as well as to commercial cells, applications, and Li-ion pack products. Testing of the Phase II design shall include mock manufacturing runs using small production batches of Li-ion 6T cells and Li-ion 6T batteries. Integration of the technology developed and demonstration on an existing Li-ion 6T manufacturing process and production line line capable of at least 200 packs/month is expected in this phase. The scalability of the technology to high-volume Li-ion 6T production of up to 2000 packs/month should also be demonstrated based upon throughput and rate capabilities of the end-of-line tester and cell selector. A bill of materials and volume part costs for the Phase II design should also be developed. 

PHASE III: This phase will begin installation and integration of the solutions developed in Phase II into military Li-ion 6T and commercial Li-ion pack production processes and into low- to high-volume manufacturing lines. 

REFERENCES: 

1: Lambert, Simon M., et al. "Rapid nondestructive-testing technique for in-line quality control of Li-ion batteries." IEEE Transactions on Industrial Electronics 64.5 (2017): 4017-4026.

2:  Wu, Yi, et al. "Analysis of Manufacturing-Induced Defects and Structural Deformations in Lithium-Ion Batteries Using Computed Tomography." Energies 11.4 (2018): 925.

3:  Seo, Minhwan, et al. "Detection Method for Soft Internal Short Circuit in Lithium-Ion Battery Pack by Extracting Open Circuit Voltage of Faulted Cell." Energies (19961073) 11.7 (2018).

4:  Wolter, M., et al. "End-of-line testing and formation process in Li-ion battery assembly lines." Systems, Signals and Devices (SSD), 2012 9th International Multi-Conference on. IEEE, 2012.

5:  Parthiban, Thirumalai, R. Ravi, and N. Kalaiselvi. "Exploration of artificial neural network [ANN] to predict the electrochemical characteristics of lithium-ion cells." Electrochimica Acta 53.4 (2007): 1877-1882.

6:  Gogoana, Radu, et al. "Internal resistance matching for parallel-connected lithium-ion cells and impacts on battery pack cycle life." Journal of Power Sources 252 (2014): 8-13.

7:  "Performance Specification: Battery, Rechargeable, Sealed, 6T Lithium-ion," MIL-PRF-32565, https://assist.dla.mil.

KEYWORDS: Manufacturing, Lithium-ion, 6T, End-of-line Testing, Modeling, Simulation, Batteries, Power, Energy 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Design and build an electronic signal detection and characterization unit that utilizes artificial intelligence (AI) and machine learning (ML), that can perform continuous monitoring of the electromagnetic spectrum (EMS), and that can provide signal characteristics to an interface. 

DESCRIPTION: Recent advances in the computing world has allowed for algorithmic advances in the detection and characterization of the electromagnetic spectrum (EMS). Specifically, the incorporation of such things as neural networks and training processes has elevated artificial intelligence (AI) and machine learning (ML) as key innovation areas for detecting, characterizing and cataloging highly complex signal types in the EMS. The current effort would mature these AI/ML concepts to develop a signal detection and characterization system for electronic signals. The unit would be able to detect and characterization various signal types and modulations. It would also provide performance and monitoring tools to provide real-time feedback to operators. The incorporation of data analytics for validation and visualization would be included in the unit. The system would follow a Modular, Open Systems Approach (MOSA) to allow integration into a variety of Army systems. The MOSA approach would also provide extensible ML and Deep Learning (DL) functions to expand upon key features and signal types. The system would contain only Commercial, Off-The-Shelf (COTS) products. 

PHASE I: Develop system design that includes artificial intelligence (AI) and machine learning (ML) algorithms and concepts, hardware and software specifications, and protocol operation (both internal and external). 

PHASE II: Develop and demonstrate a prototype system in a realistic environment. Conduct testing to prove feasibility over extended operating conditions. 

PHASE III: This system could be used in a broad range of military and civilian communication applications where equipment is susceptible to electromagnetic interference - for example, in military exercises/operations or in enhancing critical industrial operations in electromagnetic saturated environments. Integrate the product as a prototype adjunct to an already existing tactical system/architecture. Demonstrate that the product can be integrated and utilized in a tactical system with minor modifications to include form, fit, function changes and minor interface upgrades. Demonstration will provide key decision points on interoperability, MOSA integration, and tactical feasibility. 

REFERENCES: 

1: Szepesvari, Caleb. Algorithms for Reinforcement Learning. 2009

2:  Ioffe, Sergey and Christian Szegedy. Batch Normalization: Accelerating Deep Network Training by Reducing Internal Covariate Shift. 2015

3:  Kinds of RL Algorithms. https://spinninup.openai.com/en/latest/spinningup/rl_intro2.html. 2018

4:  Bharati, K Swetha and Ashok Jhunjhunwala. Implementation of machine learning applications on a fixed-point DSP. 2015

KEYWORDS: Artificial Intelligence, Machine Learning, Deep Learning, Signal Detection, Signal Characterization, Modular Open Systems Approach (MOSA), Commercial Off-The-Shelf (COTS) 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: Enhancement of current Aerostat capabilities to provide Low Cost Persistent Intelligence, Surveillance and Reconnaissance (LCP ISR)) during high intensity conflicts with Class A adversaries. 

DESCRIPTION: While Aerostat systems are an essential tool for support to ongoing combat operations their utility is limited during high intensity conflicts due to their static nature, inability to rapidly redeploy within theater and inability to provide persistent Intelligence, Surveillance and Reconnaissance (ISR) in support of Wide Area Operations. Despite these shortfalls Aerostats are in high demand from our coalition partners. It is anticipated that the airship functionality could potentially be obtained thru normal P3I efforts and little to no additional program costs. Our fires community can provide strategic fires hundreds of miles further than our current sensors can currently provide persistent coverage. UAV and space based assets are vulnerable to enemy targeting and are too expensive to provide persistent low cost wide area coverage. Once targeted UAV and space based sensors are difficult and expensive to reconstitute in any reasonable period of time. Desire is to implement P3I initiatives against our current Aerostat system which would provide immediate enhanced capabilities in regards to persistent & low cost wide area ISR while leveraging the current Aerostat infrastructure currently deployed. Follow on efforts would further scale this capability for use in tactical, operational and strategic missions. This would provide the Army and the department of defense a significant operational capability for Force Protection, Cyber, and Precision Fires all of which are critical capabilities for battlefield dominance and would provide a substantial procurement & sustainment savings over our current operations. Effort would enable Aerostats to operate autonomously or as remote controlled unmanned Airships that can be statically deployed via tethers as they are now but with the ability to drop its tether and self-deploy within its theater while conducting limited wide area operations LCP ISR. Endurance for static operations would be 30 days continuous operations and 7 days during airship mode operations with an operational range of 2000 miles. While these systems would be vulnerable to enemy targeting and destruction, the systems would be considered attritable and due to their low cost; easily replaceable. It is anticipated that enemy action would be counterproductive due to the necessary enemy disclosure that would result. 

PHASE I: Carry out a feasibility study for leveraging current commercial Airship designs for military use and demonstrate potential capabilities via use of commercial products as military prototypes. Phase I will define factors for a Phase II sensor demonstration for Fires, Cyber, and Force Protection. 

PHASE II: Demonstrate capabilities using the commercial prototype for Fires, Cyber and Force Protection. 

PHASE III: Develop prototype (aka battle type) that would be deployed into a combat theater for proof of concept assessment. Potential DoD customers/transition partners include Army program-of record Force Protection systems, US Marine, Navy Command units, USAF Security force operations, Coast Guard, Customs and Border Patrol, Nuclear Energy Commission, Homeland Security (Cruise Missile Defense) and Foreign Military Sales. 

REFERENCES: 

1: A. F. L. Deeson, An Illustrated History of Airships (Bourne End, Bucks: Spurbooks Limited, 1973), 15-20.

2:  R. P. Largess, "Reviving the Naval Airship," NAVAL FORCES vol XI, No 1 (1990): 13.

3:  David Brinkman, "Sentinels in the Sky," JANE’S DEFENCE WEEKLY vo I 15, no 3 (19 Jan 91): 89.

4:  "Potential Military Use of Airships and Aerostats," Congressional Research Service, www.crs.gov, RS21886, September 1, 2006.

5:  D. E. Ryan, Jr., "The Airship's Potential for Intertheater and Intratheater Airlift," Thesis at School of Advanced Airpower Studies Air University, Maxwell Air Force Base, Alabama, May, 1992.

KEYWORDS: Aerostat, LCPISR, Unmanned-airship 

TECHNOLOGY AREA(S): Electronics 

OBJECTIVE: The Army has interest in sensors with passive and low probability of intercept acquisition and weapon cueing capabilities applicable to air defense in support of Short Range Air Defense (SHORAD) system missions. Small innovative business insights to support highly survivable short to moderate range Army Air and Missile Defense (AMD) acquisition and fire control sensors initiatives is sought. 

DESCRIPTION: State-of-the-Art or emerging passive or low probability of intercept sensor technologies are needed as complementary components of the SHORAD integrated sensor suite to support SHORAD unit real time Situational Awareness (SA), target acquisition and weapon cueing. The SHORAD missions require rugged, responsive, compact high precision sensors, which are capable of supporting targeting (weapon cueing as a minimum), identification/recognition and data fusion processes, while producing a reduced signature to threat counter Intelligence, Surveillance and Reconnaissance (ISR) assets. On-board passive and low probability of intercept sensors must be compatible with supported unit battlefield environments and vehicle form factors. It is expected that these requirements will drive integration of multi-spectral passive sensor / low probability of detection sensor technologies in rugged, compact form factors. The prioritized targets to be addressed are: 1. Nano- to Class III Unmanned Air System (UAS), to include individual, multiple and swarm presentations. 2. Rotary Wing/Fixed Wing (RW/FW), to include countering aircraft launched Tactical Air to Surface munitions. 3. Rocket, Artillery and Mortar (RAM) to include precision indirect fires and salvo attacks. Sensors are required to perform target acquisition at all mission phases and to support target engagement on the move or on a short halt. Preference is for the sensor to support high volume of fire required to a large number of different target types in a combined saturation attack. Sensors are required to perform target acquisition at all mission phases and to support target engagement on the move or on a short halt. Preference is for the sensor to support high volume of fire required to a large number of different target types in a combined saturation attack. Sensor related elements of the kill chain include: 1. Target acquisition. 2. Fusion with other SHORAD sensors. 3. Positive identification, Identification of Friend or Foe (or classification of non-combatant). 4. Weapon cueing (with possible fire control capability) and kill assessment of kinetic and non-kinetic engagements. 

PHASE I: Investigate and research technologies that can be incorporated into SHORAD systems, and are complementary to existing SHORAD sensors, to build and field sensor systems that are extremely difficult to detect, or attack, and are able to provide actionable information to the Soldier concerning active threats. Some technologies may be commercial-off-the-shelf tools that can be innovatively employed to operationally harden systems (operate with minimal signature in the battlefield ground mobile environment). Some technologies may be new and, as yet, not well known. False targets must be minimized, but sensors must provide actionable data in real time. Sensors could be signature based, behavior based or may leverage a technique that is yet to be developed. Sensors must be compatible with, or tolerate, periodic system software updates/patches, must be “soldier friendly” and supportable throughout the lifetime of the fielded system. Investigations should include estimated development and production costs (to support preliminary government budgeting activities). Once investigation and research of potential technology is complete, the offeror will, in an unclassified format, identify implementation options in a Phase 1 report. 

PHASE II: Using the technology and approach(es) identified in Phase I, and adding classified Phase II technologies if needed, develop, fabricate and validate a prototype sensor. The sensor should fully address integration, size-weight-and-power (SWAP), and any system performance or impacts. A technology Readiness Level (TRL) of 5 or 6 depending on system complexity and SHORAD system availability (TRL 5 - Component and/or breadboard validation in relevant environment / TRL 6 - System/subsystem model or prototype demonstration in a relevant environment) is required to support initial sensor evaluation activities and possible incorporation into the SHORAD equipment set. Given a viable technical approach and performance, estimate and refine development, support and production costs to be included with technical concept data and delivered prototype implementation. 

PHASE III: Transition the Phase II product into a fieldable sensor prototype for detailed technical and operational testing. Following testing, perform cost/ manufacturability/ performance optimization and prepare sufficient data products to support potential procurement and fielding with the Army AMD sensors, weapons, and/or with other potential systems. 

REFERENCES: 

1: DETECTION AND JAMMING LOW PROBABILITY OF INTERCEPT (LPI) RADARS, NAVAL POSTGRADUATE SCHOOL MONTEREY, CALIFORNIA THESIS, Aytug Denk, September 2006, http://dtic.mil/dtic/tr/fulltext/u2/a456960.pdf

2:  Emission Management for Low Probability Intercept Sensors in Network Centric Warfare, Vikram Krishnamurthy, University of British Columbia, IEEE Transactions of Aerospace and Electronic Systems VOL. 41, NO. 1 January 2005, www.ece.ubc.ca/~vikramk/Kri05.pdf

3:  DETECTION AND CLASSIFICATION OF LOW PROBABILITY OF INTERCEPT RADAR SIGNALS USING PARALLEL FILTER ARRAYS AND HIGHER ORDER STATISTICS, NAVAL POSTGRADUATE SCHOOL, Monterey, California THESIS, Fernando L. Taboada, September 2002, http://www.dtic.mil/dtic/tr/fulltext/u2/a407164.pdf

4:  Bi- and Multistatic Radar, Terje Johnsen and Karl Erik Olsen, Norwegian Defence Research Establishment (FFI), Advanced Radar Signal and Data Processing (pp. 4-1 – 4-34). Educational Notes RTO-EN-SET-086, Paper 4. Neuilly-sur-Seine, France: RTO. RTO-EN-SET-086, http://www.dtic.mil/dtic/tr/fulltext/u2/a470685.pdf

KEYWORDS: Passive Sensor, Electro-optical/Infra-red, Bi-static, Multi-static, Low Probability Of Intercept, Weapon Cue 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Improve ballistic performance of the HGU-56P helmet through retrofit or replacement of the helmet shell and/or lining foam. 

DESCRIPTION: Improved armor protection is a fundamental component of lethality, one of the six army modernization priorities of the Army. Current ballistic protection of the HGU-56P helmet is limited to a .22 caliber, 17-grain, T37 FSP. Multiple ballistic material technologies have been published in the last year suggesting ballistic improvement to the aviation helmet can be achieved with minimal weight increase. These include graphene: https://www.azonano.com/article.aspx?ArticleID=3934 Diamene: https://www.materialstoday.com/carbon/news/diamene-looks-like-graphene-acts-like-diamond/ Nanomaterials: http://zeenews.india.com/news/space/paper-thin-material-that-can-stop-flying-bullets-created_811129.html Sheer thickening fluids: http://www.foxnews.com/us/2017/06/02/air-force-cadet-creates-bulletproof-breakthrough.html Structured polymer composites: https://theweek.com/articles/470303/bulletproof-super-material-thats-paperthin Composite metal foam: https://www.dailymail.co.uk/sciencetech/article-3529765/The-bulletproof-FOAM-turns-gunshot-dust-Material-used-make-lightweight-body-armour-protect-cars.html This solicitation intends to identify ballistic improvement solutions that can be applied to the existing helmet as a retrofit or replacement of the shell or foam with the least amount of weight increase and/or structural changes and quantify the improvement. Objective is to provide US National Institute of Justice (NIJ) Level II (9mm) ballistic protection. Current helmet shell protection is called out in 1680-ALSE-101, Aircrew Integrated Helmet System Fabrication Specification. 

PHASE I: This effort shall create a study identifying the most promising ballistic improvement technologies allowing retrofit of the aviator helmet with the lowest weight and cost to enable production. The study shall also project durability and retrofit time for each solution. A demonstration of ballistic performance of the technology proposed is required. Options for introduction of the new material(s) proposed include retrofit of the existing helmet (most desirable), replacement of the helmet shell, replacement of the helmet liner foam, or replacement of both the liner and foam (lease desirable). Ballistic improvement can be projected as a function of keeping total helmet weight equal or less than existing helmet of each size. I.e., if technology proposed will not improve ballistic performance over existing helmet weight, than that technology should be considered a "no-go". A threshold requirement of 10% ballistic improvement to the existing helmet is required as an entry criteria for Phase II. 

PHASE II: The best two solutions identified in phase I will be used to build or retrofit a helmet and tested to quantify ballistic improvement. Four helmet(s) will be furnished to the vendor for retrofit and ballistic testing. The retrofit process for the helmet will be documented for each solution. A summary report at the end of the study shall document ballistic performance improvement of each solution, identify exact weight impact to the helmet, identify retrofit time and cost of each solution and assess durability of each solution. If acceptable ballistic improvement is found without unacceptable increase in weight, a new set of tests will be performed to ensure the helmet still meets all requirements of the PRODUCT SPECIFICATION, Aircrew Ballistic Helmet (ABH), HGU-56/P Shell and Maxillofacial Shield (MFS). The contractor shall update the product specification with the new ballistic performance capability to reflect the improved armor protection and a projection of increased weight based on prototype production. Perform bench testing for all helmet specification requirements on production representative prototypes. Government will supply an additional thirty six (36) helmets to be retrofitted to support bench and field test/evaluation for all requirements of the helmet specification. Deliverables will include test plan, test report, updated helmet specification reflecting measured improvement in ballistic performance, minutes for all meetings conducted with the vendor, presentation slides for retrofit application of ballistic material, a white paper detailing the retrofit process of the ballistic material, and a cost report detailing retrofit cost as a function of helmet quantity from a minimum of 50 and up to 1000 at a time. 

PHASE III: Develop production processes for best retrofit solution found in Phase II. Update the helmet item specification to reflect final production process weight. Aviation helmets used throughout DOD may find retrofit application for this same process. Commercial jet engines may find an ultra light coating application capable of resisting turbine blade failure causing injury or death to a passenger aircraft. 

REFERENCES: 

1: http://www.foxnews.com/us/2017/06/02/air-force-cadet-creates-bulletproof-breakthrough.html

2:  http://zeenews.india.com/news/space/paper-thin-material-that-can-stop-flying-bullets-created_811129.html

3:  https://www.azonano.com/article.aspx?ArticleID=3934

4:  https://www.materialstoday.com/carbon/news/diamene-looks-like-graphene-acts-like-diamond/

5:  https://www.siliconrepublic.com/machines/mass-produce-graphene-solved

6:  https://theweek.com/articles/470303/bulletproof-super-material-thats-paperthin

7:  https://www.dailymail.co.uk/sciencetech/article-3529765/The-bulletproof-FOAM-turns-gunshot-dust-Material-used-make-lightweight-body-armour-protect-cars.html

KEYWORDS: Aviation Helmet, Ballistic Performance 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop, design and fabricate a Soldier wearable power generation device that can provide power in all operational environments across the range of military operations from training, full-scale war and counter-insurgency operations to peacekeeping, support and reconstruction operations. This topic addresses lighter tactical power generation that increases the ability to operate semi-independently; a critical enabling technology to the Soldier Lethality Army Modernization Priority. 

DESCRIPTION: Currently, the individual Soldier's mobility is constrained, in part, by the necessity to carry extra batteries and/or man-portable power generation and battery charging equipment, to meet the power demands of the equipment he/she carries. The Power Generation for Individual Soldier device shall provide a minimum of 6 watts of continuous uninterrupted power for 24 hours. The device, including fuel source as applicable, shall have a volume not to exceed 50 cubic inches and shall not weigh more than 2.5 pounds (lbs). No dimension shall exceed 12 inches. It shall operate during day and night. 

PHASE I: Develop overall system design and provide a performance specification as part of the Final Technical Report. Include unit cost projections in the Technical Report. A breadboard demonstration of proposed design is encouraged. 

PHASE II: Design, fabricate and demonstrate a prototype system in an operational relevant environment. Deliver two TRL 6 prototypes to the Government. Deliver Final Technical Report, which includes a product specification and estimated unit production cost. 

PHASE III: A wearable power generation system has multiple uses in military and civilian operations. Besides the obvious first responders' and outdoors' types of applications, this device could potentially end the current problem with handheld and other power consuming devices, where their batteries run out of power before consumers have a chance to find a place to plug in. With the constant growth of wireless services and the capabilities of wearable devices, current battery technology is not keeping up with power consumption. This could be the solution. Phase III shall consist of the development of the producibility of this item for military use. 

REFERENCES: 

1: Stirling engine, from Wikipedia, the free encyclopedia

2:  Renewable energy, from Wikipedia, the free encyclopedia

3:  Photovoltaics, from Wikipedia, the free encyclopedia

4:  Biofuel, from Wikipedia, the free encyclopedia

5:  Photosynthesis, from Wikipedia, the free encyclopedia

6:  Micropower, from Wikipedia, the free encyclopedia

KEYWORDS: Wearable, Power, Generation, Continuous, Lightweight, Small 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: To increase overall Soldier Lethality Capability by providing ballistic calculators, weapon fire control devices, and related apps, with immediate, real-time muzzle velocity information after each shot fired to automatically update ballistic computations to enhance accuracy of follow-on shots. 

DESCRIPTION: Muzzle velocity is the speed of a projectile at the moment it leaves the muzzle of a gun and a key parameter in determining a projectile’s external/exterior ballistics (i.e. flight profile and trajectory). Small arms exterior ballistic calculations, used to predict an aim point in order to hit a target, are based on either estimated muzzle velocities or measured muzzle velocities which are typically taken when zeroing a weapon and before executing a mission. However, muzzle velocities will typically change over time and during operational-use based on several dynamic factors to include barrel cleanliness and wear; rate-of-fire; variations in ammunition composition; ammunition and bore temperatures; and (when available) weapon suppressor conditions. Real-time muzzle velocity measurements, provided in a closed-loop feedback schema, would allow fire control and ballistic calculators to better account for and compensate for these unknown and constantly changing variables, thereby increasing aiming accuracy and probability of (target) hit on successive shots. It is envisioned that this measuring device would eventually be affixed to or incorporated within a weapon barrel. The closed loop feedback between the muzzle velocity measurement device and ballistic solver(s) would be accomplished via either hard-wired or wireless communications. This effort would ultimately increase mission effectiveness and overall soldier lethality. 

PHASE I: Research and propose a viable cost-effective technical solution that satisfies the stated objective. In order to expedite an initial proof of concept, PMSW would like to focus on applying this desired capability to current medium-to-long range sniper weapons since 1) sniper teams require the utmost in aiming accuracy and 2) they currently rely on muzzle velocities with ballistic solvers in determining scope reticle offset holds for target engagements. Potential applicable sniper weapon platforms for consideration include the 7.62mm M110 Semi-Automatic Sniper System (SASS), the .300WinMag M2010 (bolt-action) Enhanced Sniper Rifle (ESR), .50 Cal M107 (semi-auto) Long Range Sniper Rifle (LRSR), and future Precision Sniper Rifle (a multi-caliber 7.62mm/.300NM/.338NM weapon). It is envisioned that once proven, the technology could be scaled to other mission area weapons as fire control capabilities proliferate, especially with Next Generation Squad Weapons. As such and to facilitate Phase I efforts, a surrogate sniper weapon, optic, and ammunition, comparable to the M110, should be used. Likewise, use of a surrogate (computer/smart-phone based) fire-control ballistic solver would be acceptable, but ultimately, PMSW would like initial integration with the Kestrel 5700 Elite Weather Meter with Applied Ballistics, which was recently adopted in Fiscal Year (FY) 2017 by the Army as its Ballistic Weather Meter (BWM) and added as a component to the Advanced Sniper Accessory Kit (ASAK). PMSW would also like the measurement accuracy of this device to be within +/- 1% of the actual (Doppler radar measured) bullet muzzle velocity. This accuracy is commensurate with the Government tested accuracy of the Magnetospeed Ballistic Chronograph (Part #: MS V3BT), which was also adopted by the Army, as its Small Arms Ballistic Chronograph (SABC), and added to the ASAK in FY 2015. Some other investigative constraints to consider include 1) that size and/or form factor does not adversely affect shooter operation; 2) that the device can be mounted/installed in conjunction with and will not interfere with other existing or planned weapon devices (such as existing mounting rails, suppressors, bipods, sight posts, etc…); 3) that the device must not alter the inherent baseline accuracy of the host weapon system; 4) that the device can withstand and operate within anticipated weapon operational shock and temperature ranges; and 5) that the device shall be able to operate within and not adversely contribute to Electromagnetic Environmental Effects (E3). The proposed solution should be the result of an engineering tradeoff analysis conducted among several possible courses of action with a focus on SWaP-C (size, weight, power & costs) considerations. The analysis should detail technical advantages/disadvantages, as well as technical/programmatic risks, and provide rough cost estimates for a fieldable technology. All work performed in Phase I shall be provided in a final report that identifies the best conceptual solution. Breadboard tests to demonstrate technical feasibility are encouraged. 

PHASE II: Design, develop, build, and deliver six (6) prototype Real-time Muzzle Velocity Feedback Systems based on Phase I recommendations that can be demonstrated with a weapon platform that is comparable to the M110 SASS. The M110 SASS is a militarized variant of the commercially available 7.62mm SR-25 from Knight’s Armament Company. The RMVFS is intended to integrate with a ballistic solver software to effectively use that muzzle velocity data to calculate real-time exterior ballistics and provide any adjusted aim-points. The system needs to be tested to prove that the RMVFS muzzle velocities meet the objective accuracy requirements and that muzzle velocity data can be passed and used in real-time by a ballistic solver. Phase II culminates with a report that includes test and demonstration results. A detailed proposal will be developed that delineates required efforts to have a TRL-7 system available to be demonstrated in a military environment as a potential Phase III follow-on effort. 

PHASE III: In conjunction with a military customer, optimize and ruggedize the Phase II prototype system for possible integration with Army small arm fire control systems / ballistic solvers and insertion within Army combat teams. The system has potential commercial applicability for law enforcement, hunters, and target shooters. 

REFERENCES: 

1: "Truing" How-to Calibrate Your Ballistic Solution - Long-range Shooting | Applied Ballistics, National Shooting Sports Foundation (NSSF) https://www.youtube.com/watch?v=lUDdnWT7vyI, 19 July 2017

2:  Chronograph Accuracy Tips – 15 Practical Tips to Increase Accuracy & Reliability, http://precisionrifleblog.com/2012/07/20/chronograph-accuracy-tips-15-practical-tips-to-increase-accuracy-reliability/, 20 July 2012

3:  Lessons Learned from Ballistic Coefficient Testing - Exterior Ballistics.com, http://www.exteriorballistics.com/ebexplained/5th/24.cfm.

4:  External Ballistics, https://www.hornady.com/team-hornady/ballistic-calculators/ballistic-resources/external-ballistics

5:  Howard Hall, External Ballistics Part II – Flight to Target, in Ballistics, http://aegisacademy.com/external-ballistics-part-ii/ , 18 June 2014

6:  Ryan Cleckner, Ballistics Basics: Initial Bullet Speed, https://gundigest.com/more/how-to/training/ballistics-initial-bullet-speed, 20 October 2017

7:  Nicholas G. Paulter, Jr., Donald R. Larson, Reference Ballistic Chronograph, Optical Engineering 48(4), 043602, April 2009, https://ws680.nist.gov/publication/get_pdf.cfm?pub_id=32808

KEYWORDS: WEAPON, AMMUNITION, MUZZLE VELOCITIES, AIM POINT, FIRE CONTROL, EXTERNAL, EXTERIOR, BALLISTIC CALCULATIONS, CHRONOGRAPH 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: This project seeks the development of an additive powder with the same composition as the lightweight armor steel, FeMnAl, for future repair of components made of this steel, and design of new components. 

DESCRIPTION: FeMnAl is a lightweight, high-strength steel alloy with Fe-28Mn-9.5Al-1Si-0.5Mo-0.9Cdeveloped for armor applications. The Army is interested in using this steel to reduce weight in a variety of ground vehicle platforms. While a high-alloy steel, it is a single phase, with age-hardenability. This means there are fewer concerns with rapid solidification, as martensite cannot form, and heat treatment can be used to control the hardness of the final part. Similarly, there is growth in the development of additive manufacturing repair techniques for ground vehicles. However, there is not currently a similar high-alloy steel powder available. Additive repairs requires compatibility with this high alloy steel, which in turn requires unique powder compositions. The unique chemistry of this alloy is expected to be challenging, and require innovative processes to manufacturing in powder form. This steel has been produced via traditional metal manufacturing techniques, in both cast and wrought forms. No attempt has been made to develop a powder form of this material. 

PHASE I: In Phase I, the small business will assess the capability to make high alloy powders near this composition. This powder will be compatible with Directed Energy Deposition, with a powder size of 60 to 125µm. Compositional validation will be required. High rating will be placed on compositional evaluation using wet chemistry methods, due to known limitations of optical emission and spark spectroscopy for this composition. Feasibility of process will be demonstrated by production of a small batch of powder of the intended composition. Deliverables shall include materials data and physical powder samples. 

PHASE II: In Phase II, the small business will improve processing to make powder within compositional tolerances, targeting uniformity throughout the batch. This phase will include characterization of the powder produced by various metrics [Slotwinski], and manufacture of test articles, such as density, hardness, and metallographic samples. The final deliverable will include: • Composition testing results • Material test results • Documentation of powder characteristics (size distribution, particle density, particle morphology, particle crystalline phases) 

PHASE III: In the final Phase of the project, the contractor will determine capability to produce the powder in larger scales, and develop a strategy for qualification. The final powder should easily transition to customers interested in light weighting, particularly in wear-sensitive regions. Powder would be made available to Programs of Record, such as PdM Abrams, for purchase and use for repair of their systems in which FeMnAl has been integrated. It may also be used in future design of specific components with significant weight restrictions. 

REFERENCES: 

1: Zimmerman, B, Allen, E., "Analysis of the Potential Impact of Additive Manufacturing on Army Logistics", Naval Postgraduate School Monterey Ca, (Dec 2013). http://www.dtic.mil/get-tr-doc/pdf?AD=ADA620821

2:  Slotwinski, J.A., et. al. "Characterization of Metal Powders Used For Additive Manufacturing", J. Rsch. NIST (2014). https://nvlpubs.nist.gov/nistpubs/jres/119/jres.119.018.pdf

3:  Howell, R.A. "Microstructural influence on dynamic properties of age hardenable FeMnAl alloys", Missouri University of Science and Technology (2009). http://scholarsmine.mst.edu/doctoral_dissertations/1940/

4:  "DoD Additive Roadmap" https://www.americamakes.us/our_work/technology-roadmap/

5:  University of Loughborough, "About Directed Energy Manufacturing" http://www.lboro.ac.uk/research/amrg/about/the7categoriesofadditivemanufacturing/directedenergydeposition/

KEYWORDS: Steel, Additive Manufacturing, Powder Metallurgy, Metallic Alloys 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Development of a man-portable 2kW SOFC system with 13kW power spikes. System to power robotic vehicles, ground vehicle auxiliary systems or exoskeletons. System durability will be increased as well. 

DESCRIPTION: Solid Oxide Fuel Cell (SOFC) systems allow for power generation using hydrocarbon fuels (such as JP-8, propane, butane or methane) which are readily available, instead of hydrogen gas, which is not as easily obtainable and requires additional storage and/or equipment to use and produce. In addition, SOFC systems also have high power densities (1), high electrical efficiencies (1), a lower acoustic signature than internal combustion engines (2), produce water as a byproduct (3), have the highest tolerance for sulfur in the fuel of any fuel cell type (3) and do not require the use of precious metal catalysts for operation (3). These advantages make SOFC systems (i.e. stack and balance of plant components) useful as auxiliary power sources to charge batteries on robotic vehicles and exoskeleton systems, run peripheral equipment to alleviate power consumption from the main power plant, export power from the vehicle to power stationary devices and have the ability to run near-silent for silent watch operations. Despite these advantages, SOFC stack technology used in today’s light-weight, man-portable systems are not capable of suppling enough power in the space-claim provided and also have low system durability. Smaller scale SOFC systems currently exist that would fit into a similar space claim as proposed here, but the power supplied by those systems is lower than 2kW. The 2kW of power generated by the SOFC stack, with the system capable of up to 13kW intermittent power spikes using internal batteries, proposed in this topic is viewed as an adequate starting power for use with robotic vehicles, auxiliary systems on ground vehicles and exoskeleton systems. Advancement of new novel materials used within the system construction (such as catalysts used in electrode construction and oxygen transport materials used in electrolyte construction), increased catalyst loading, optimized system design and innovative geometries used in stack design to increase active surface area can all be investigated and developed to address this issue. The SOFC system (i.e. SOFC stack, internal batteries for 13kW power, fuel and balance of plant components) will have the following requirements in addition to meeting the 2kW power. The system will have a power density of at least 94 W/kg or have a total mass of 45 kg while having a total system volume of 4,000 cubic inches or less. The system will produce 36-48V of electricity and be able to supply power using the attached fuel source for 4-5 hours continuously. The system will be able to thermally cycle between 50-100 times without the SOFC system power degrading below 2kW (excluding internal battery power). The system will be able to operate for at least 1,000 hours (combined operation time or single continuous use) without the SOFC system power degrading below 2kW (excluding internal battery power). The system will have a start time of 30 minutes or less to achieve 2kW of continuous power with 13kW intermittent power. The target system cost, for commercialization purposes, is expected to be between $5,500/kW and $8,000/kW based on projected system costs from the DOE. The system will be capable of being operated with compressed hydrogen gas or with light hydrocarbon fuels (such as butane, propane or methane). These system requirements are standard with less compact SOFC systems, which should be preserved for this more compact system as well (4), (5). 

PHASE I: This phase will focus on conducting a feasibility study to determine the best approach to achieve the SOFC systems requirements listed above. This study will be used to identify materials and different fabrication approaches that will allow the SOFC system to achieve the desired system power output. The feasibility study will also focus on methods of increasing system durability and methods of eliminating failure points during operation. 

PHASE II: Phase II will focus on optimizing the SOFC system design and conducting durability experiments. Experiments will be conducted in stages first by using single cells or short stacks (5-cell stacks). Stack size will then gradually be increased and each new stack size will be tested to identify degradation and durability failure modes until a full stack passes testing criteria. SOFC system power will be increased to 2kW by conducting experiments on the system to identify points of parasitic losses and novel approaches of manufacturing the SOFC system to minimize those losses through different material choices or system design. A preliminary investigation should also be completed in order to determine the cost of fabricating the SOFC devices and stacks. 

PHASE III: The system should be scalable to provide power to the military in such areas as: 1. Robots and exoskeletons used for reconnaissance and bomb disposal, 2. Drone aircraft used for reconnaissance and short to medium ranged strikes, and 3. Auxiliary power to ground vehicles to save energy costs and for silent watch capability. The system should also be scalable for the commercial market to provide power in areas of: 1. Power generation for homes, 2. Auxiliary power for ground commercial vehicles, and 3. Auxiliary power for light commercial aircraft. The system should also conform to particular dimensions of a space claim and provide the required amount of power for each application. 

REFERENCES: 

1: Y. Li et al., Energies, 8, (2015), http://www.google.com/url?sa=t&rct=j&q=&esrc=s&source=web&cd=27&ved=0ahUKEwia_YzW8ufTAhUq54MKHcQKCZg4FBAWCEswBg&url=http%3A%2F%2Fwww.mdpi.com%2F1996-1073%2F8%2F3%2F1896%2Fpdf&usg=AFQjCNG01yLyw-Cotgmq_PQplkF3VJflCA&sig2=E4AVjBfZZaWaFAIykT4y_w

2:  National Research Council, Meeting the Energy Needs of Future Warriors, (2004), https://books.google.com/books?id=Z6BVAgAAQBAJ&pg=PA23&lpg=PA23&dq=SOFC+lower+acoustic+signature&source=bl&ots=4Sx1FqL1Df&sig=4_IhylmWerrb2m0SGNzYEpvmeEk&hl=en&sa=X&ved=2ahUKEwjM7cvow7jdAhWE0VMKHRwqBd8Q6AEwAXoECAkQAQ#v=onepage&q=SOFC%20lower%20acoustic%20signature&f=false

3:  Office of Energy Efficiency & Renewable Energy, Fuel Cell Technology Office, (2018), https://www.energy.gov/eere/fuelcells/types-fuel-cells

4:  Atrex Energy, Product Specification, http://www.atrexenergy.com/services-resources/technical-information

5:  Protonex, P-200i SOFC Technical Specifications, https://protonex.com/wp-content/ uploads/2016/04/ Protonex-P200i.pdf

KEYWORDS: Solid Oxide Fuel Cell, Fuel Cell, Alternative Energy, Auxiliary Power, Exportable Power, Ground Vehicles, Robotics, Exoskeleton 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: This is an AF Special Topic in partnership with AFWERX, please see the above AF Special Topic instructions for further details. A Phase I award will be completed over 3 months with a maximum award of $50K and a Phase II may be awarded for a maximum period of 27 months and $1,500,000. The objective of this topic is to explore Innovative Defense-Related Dual-Purpose Technologies that may not be covered by any other specific SBIR topic and thus to explore options for solutions that may fall outside the Air Force’s current fields of focus but that may be useful to the US Air Force. An additional objective of this topic is to grow the industrial base of the US Air Force. This topic will reach companies that can complete a feasibility study and prototype validated concepts in accelerated Phase I and II schedules. This topic is specifically aimed at later stage development rather than earlier stage basic science and research. 

DESCRIPTION: The Air Force is a large and complex organizations that consists of many functions that have similar counterparts in the commercial sector. We are interested in exploring innovative technology domains that have demonstrated clear commercial value in the non-defense sector (i.e., through existing products/solutions) in order to see if they have similar Air Force applications (i.e. Dual-Purpose Technologies/Solutions). We recognize that it is impossible to cover every technological area with the SBIR topics, thus this topic is intended to be a call for open ideas and technologies that cover topics that may not be currently listed (i.e. the unknown-unknown). It is important that any potential solutions have a high probability of keeping pace with the technological change and thus should be closely tied to commercial technologies and solutions that will help support the development of the solution. This topic is meant for innovative non-defense commercial solutions to be adapted in innovative ways to meet DoD stakeholders’ needs in a short timeframe and at a low cost. Solutions for this topic should be focused on the three areas listed below and should try to meet as many of these as possible. 1. Technical feasibility – There should be minimal technical risk to the overall solution. The best solutions will have demonstrated technical feasibility by showing the solution being used broadly by other customers, especially in the non-defense space. If the solution has not demonstrated technical feasibility in the non-defense space, the offeror(s) may provide alternative evidence to indicate technical feasibility such as initial lab tests, use of the product with defense customers and other forms of evidence. 2. Financial Sustainability – The offeror(s) should demonstrate financial sustainability of the solution and the offeror(s). The best solutions will demonstrate this by sales of the solution to non-defense clients and other sources of private investment. If the solution has not demonstrated financial sustainability by non-defense sales or private investment, the offeror(s) may provide other evidence of financial sustainability such as other governmental aid, sales to defense customers, and other forms of evidence that help explain the financial sustainability. 3. Defense Need – The offeror(s) should demonstrate that they have an understanding of the fit between their solution and defense stakeholders. The offeror(s) may provide an indication of a defense ‘need’ by evidence of preliminary discussions with USAF stakeholders, a clear description (including contact name, rank, unit and contact information) of a specific, potential USAF stakeholder that may need to use the solution or other forms of evidence to help explain a clear defense need. In summary - proposals for this topic should demonstrate a high probability to quickly find product-market fit between an Air Force end user and the proposed solution through adaptation of a non-defense commercial solution. This can be done through a proposal with a mature non-defense technical solution and a starting point to find an Air Force customer. BROAD FOCUS AREAS AND SPECIFIC USER NEEDS FOR 19.2 OPEN TOPIC Though the topic is truly ‘Open’ (agnostic of industry, technology, and problem area), to facilitate streamlined customer discovery for companies in Phase I, we have identified certain problem areas for which potential Air Force Customers and/or funding have already been identified. These areas, which we break out into broad ‘Focus Areas’ and specific ‘User Needs’, are described below. Focus Areas – for a broad ‘Focus Area’ to be included in this topic (the list of Focus Areas can be viewed at https://www.afwerx.af.mil/sbir.html), we required that it either have a significant number of Air Force customers seeking solutions in that area OR a specific Air Force Customer that has set aside funding to address that area by way of SBIR fund-matching. Thus, if your solution can help address one of these Focus Areas, there is likely to be a good number of Air Force End-Users and customers that you can interact with in your phase I feasibility study and an increased likelihood for matching funding. User Needs – for a specific ‘User Need’ to be included in this topic (the list of User Needs can be viewed at https://www.afwerx.af.mil/sbir.html), we required that an Air Force end-user or customer clearly articulate a specific problem affecting their mission for which they are actively seeking solutions from SBIR companies. Thus, if your solution can help address one of these User Needs, then there is *at least* one Air Force end-user that you can readily interact with in your phase I feasibility study. If you believe your solution can help address one of the ‘Focus Areas or ‘User Needs’, please note this on the first slide of your application slide deck AND include the Focus Area ID # or User Need ID # in your ‘Keywords’ in the online SBIR application (Example: FA-001, or UN-1034). The alignment between a proposal and a ‘Focus Area’ or ‘User Need’ can strengthen an application. Note that this does not change the requirement to demonstrate the defense need as listed above, but may complement it. This also does not preclude companies who are looking to solve other problems that are not listed in the ‘Focus Areas’ or ‘User Needs’ to submit to this topic; it is simply intended to give indications of areas of special focus for the Air Force at this particular point in time. 

PHASE I: Validate the product-market fit between the proposed solution and a potential USAF stakeholder and define a clear and immediately actionable plan for running a trial with the proposed solution and the proposed AF customer. This feasibility study should directly address: 1. Clearly identify who the prime potential AF end user(s) and AF transition customer (the user and customer will likely be two different people) and articulate how they would use your solution(s) (i.e., the one who is most likely to an early adopter, first user, and initial transition partner). 2. Deeply explore the problem or benefit area(s) which are to be addressed by the solution(s) - specifically focusing on how this solution will impact the end user of the solution. 3. Define clear objectives and measurable key results for a potential trail of the proposed solution with the identified Air Force end user(s). 4. Clearly identify any additional specific stakeholders beyond the end user(s) who will be critical to the success of any potential trial. This includes, but is not limited to, program offices, contracting offices, finance offices, information security offices and environmental protection offices. 5. Describe how the solution differs from the non-defense commercial offering to solve the Air Force need - (i.e. how has it been modified) 6. Describe the cost and feasibility of integration with current mission-specific products. 7. Describe if and how the demonstration can be used by other DoD or governmental customers The funds obligated on the resulting Phase I SBIR contracts are to be used for the sole purpose of conducting a thorough feasibility study using scientific experiments, laboratory studies, commercial research and interviews. Prototypes may be developed with SBIR funds during Phase I studies to better address the risks and potential payoffs in innovative technologies. 

PHASE II: Develop, install, integrate and demonstrate a prototype system determined to be the most feasible solution during the Phase I feasibility study. This demonstration should focus specifically on: 1. Evaluating the proposed solution against the objectives and measurable key results as defined in the phase I feasibility study. 2. Describing in detail how the solution differs from the non-defense commercial offering to solve the Air Force need and how it can be scaled to be adopted widely (i.e. how can it be modified for scale) 3. A clear transition path for the proposed solution that takes into account input from all affected stakeholders including but not limited to: end users, engineering, sustainment, contracting, finance, legal, and cyber security. 4. Specific details about how the solution can integrate with other current and potential future solutions. 5. How the solution can be sustainable (i.e. supportability) 6. Clearly identify other specific DoD or governmental customers who want to use the solution. 

PHASE III: PHASE III DUAL USE APPLICATIONS: This is the main goal of this topic, we intend for many of the solutions to go straight from Phase I to Phase III as soon as the product-market fit has been verified. The contractor will transition the adapted non-defense commercial solution to provide expanded mission capability to a broad range of potential government and civilian users and alternate mission applications. NOTES: a. Due to the large amount of expected interest in this topic, we will not be answering individual questions through e-mail, except in rare cases. Instead we will be holding a teleconference to address all questions in an efficient manner. This topic will be updated with the final call-in details as soon as the date is finalized. In the meantime, feel free to use the SITIS Q&A system. b. This SBIR is NOT awarding grants, and is awarding contracts, when registering in SAM.gov, be sure to select ‘YES’ to the question ‘Do you wish to bid on contracts?’ in order to be able to compete for this SBIR topic. If you are only registered to compete for grants, you will be ineligible for this topic. For more information please visit http://afwerxdc.org/sbir/ c. We are working to move fast, please register in SAMs and if already registered please double check your CAGE codes, company name, address information, DUNS numbers, ect. , If they are not correct at time of submission, you will be ineligible for this topic. In order to ensure this, please include, in your 15-slide deck, a screenshot from SAM.gov as validation of your correct CAGE code, DUNS number and current business address along with the verification that you are registered to compete for All Contracts. It is the responsibility of the contractor to ensure that the data in the proposal and the data in SAM.gov are aligned. For more information please visit https://www.afwerx.af.mil/sbir.html d. In order to keep pace with the fast timeline, if the purchase orders are not signed and returned to the contracting office within 5 business days of receipt, a Phase I award will not be issued. e. Please note that each company may only have one active ‘Open Topic’ award at a time. If a company submits multiple technically acceptable proposals, only the proposal with the highest evaluation will be awarded. If multiple proposals are evaluated to be equal, the government will decide which proposal to award based upon the needs of the Air Force. If a contractor is currently executing a Phase II award under the previous ‘Open’ topics (18.2-005, 18.3-005, 18.3-006, 19.1-004, 19.1-005), the company is ineligible for this topic. If the company applies for both the Direct to Phase II ‘Open Topic’ (192-D001) and this topic, and the company is selected for award for both topics, only the Direct to Phase II (192-D001) proposal will be awarded. All awards are subject to the availability of funds and contracting negotiations. f. The ‘DoD SBIR/STTR Programs Funding Agreement Certification’ form must be completed and signed at the time of *Proposal Submission* and can be found at: https://www.afsbirsttr.af.mil/Program/Phase-I-and-II/. g. It is the responsibility of the contractor to answer the questions in the SBIR Cover Sheet and on the ‘DoD SBIR/STTR Programs Funding Agreement Certification’ accurately. h. While these are firm fixed price contracts, it is important for the companies to include the cost volume in the SBIR online application with reasonable fidelity in order to determine the reasonableness of the proposed effort. *****Proposals submitted under this topic may relate to technologies restricted under the International Traffic in Arms Regulation (ITAR) which controls defense-related materials/services import/export, or the Export Administration Regulation (EAR) which controls dual use items. Foreign National is defined in 22 CFR 120.16 as a natural person who is neither a lawful permanent resident (8 U.S.C. § 1101(a)(20)), nor a protected individual (8 U.S.C. § 1324b(a)(3)). It also includes foreign corporations, business associations, partnerships, trusts, societies, other entities/groups not incorporated/organized to do business in the United States, international organizations, foreign governments, and their agencies/subdivisions. Offerors must identify Foreign National team members, countries of origin, visa/work permits possessed, and Work Plan tasks assigned. Additional information may be required during negotiations to verify eligibility. Even if eligible, participation may be restricted due to U.S. Export Control Laws. NOTE: Export control compliance statements are not all-inclusive and do not remove submitters’ liability to 1) comply with applicable ITAR/EAR export control restrictions or 2) inform the Government of potential export restrictions as efforts proceed.***** 

REFERENCES: 

1. FitzGerald, B., Sander, A., & Parziale, J. (2016). Future Foundry: A New Strategic Approach to Military-Technical Advantage. Retrieved June 12, 2018, from https://www.cnas.org/publications/reports/future-foundry; 2. Blank, S. (2016). The Mission Model Canvas – An Adapted Business Model Canvas for Mission-Driven Organizations. Retrieved June 12, 2018, from https://steveblank.com/2016/02/23/the-mission-model-canvas-an-adapted-business-model-canvas-for-mission-driven; 3. US Department of Defense. (2018). 2018 National Defense Strategy of the United States Summary, 11. Retrieved from https://www.defense.gov/Portals/1/Documents/pubs/2018-National-Defense-Strategy-Summary.pdf; AF192-001 SBIR ‘Open Topic’ Focus Areas – Retrieved from https://www.afwerx.af.mil/sbir.html; AF192-001 SBIR ‘Open Topic’ User Needs – Retrieved from https://www.afwerx.af.mil/sbir.html

KEYWORDS: Open, Other, Disruptive, Radical, Dual-Use, Commercial 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: This is a Pitch Day Topic, please see the above Pitch Day Topic instructions for further details. A Phase I award will be completed over 3 months with a maximum award of $75K and a Phase II may be awarded for a maximum period of 15 (or 27 month) and $750K. The objective of this topic is to explore innovative technologies that enable distributed business operations in challenging network environments and secure software and associated development environments against attacks, thus exploring options for innovative solutions that may fall outside the Air Force’s current fields of focus but that may be useful to the US Air Force. This topic will reach companies that can complete a feasibility study and prototype validated concepts in accelerated Phase I and II schedules. This topic is specifically aimed at later stage development rather than earlier stage basic science and research. 

DESCRIPTION: The Air Force Program Executive Office for Digital is responsible for the acquisition of software and weapons systems including development and fielding worldwide aerospace command and control applications. The Air Force wishes to stay at the cutting edge of these technologies and seeks to partner with innovative small businesses that may have solutions to Air Force challenges. These are the high level challenge areas for which the Air Force is interested in novel solutions: 1. Security Tools and Services: Tools to monitor the security of unclassified software development environments, to include security of on premise and cloud-hosted applications, as well as technologies that enhance the security of software development systems, pipelines, and code repositories. 2. Edge as a Service: Technologies to operate and maintain continuous and secure cloud-native operation in low-bandwidth environments. 3. Enterprise Platform Tools: Technologies for enterprise platform design, development, and delivery, as well as technologies that facilitate application and infrastructure monitoring, API management and integration, legacy system virtualization and hosting, and container orchestrations and security. This topic is meant for innovative solutions to be adapted in innovative ways to meet DoD stakeholders’ needs in a short timeframe and at a low cost. 

PHASE I: "Validate the product-market fit between the proposed solution and a potential USAF stakeholder and define a clear and immediately actionable plan for running a trial with the proposed solution and the proposed AF customer. This feasibility study should directly address: 1. Clearly identify who the prime potential AF end user(s) is and articulate how they would use your solution(s) (i.e., the one who is most likely to an early adopter, first user, and initial transition partner). 2. Deeply explore the problem or benefit area(s) which are to be addressed by the solution(s) - specifically focusing on how this solution will impact the end user of the solution. 3. Define clear objectives and measurable key results for a potential trail of the proposed solution with the identified Air Force end user(s). 4. Clearly identify any additional specific stakeholders beyond the end user(s) who will be critical to the success of any potential trial. This includes, but is not limited to, program offices, contracting offices, finance offices, information security offices and environmental protection offices. 5. Describe the cost and feasibility of integration with current mission-specific products. 6. Describe if and how the demonstration can be used by other DoD or governmental customers. 7. Describe technology related development that is required to successfully field the solution. 8. Deliver an initial prototype or minimum viable product (MVP) code or product at the conclusion of the contract that can be adapted and/or matured to a more advanced stage during Phase II. The funds obligated on the resulting Phase I SBIR contracts are to be used for the sole purpose of conducting a thorough feasibility study using scientific experiments, laboratory studies, commercial research and interviews. Prototypes may be developed with SBIR funds during Phase I studies to better address the risks and potential payoffs in innovative technologies." 

PHASE II: Develop, install, integrate and demonstrate a prototype system determined to be the most feasible solution during the Phase I feasibility study. This demonstration should focus specifically on: 1. Evaluating the proposed solution against the objectives and measurable key results as defined in the phase I feasibility study. 2. Describing in detail how the solution can be scaled to be adopted widely (i.e. how can it be modified for scale) 3. A clear transition path for the proposed solution that takes into account input from all affected stakeholders including but not limited to: end users, engineering, sustainment, contracting, finance, legal, and cyber security. 4. Specific details about how the solution can integrate with other current and potential future solutions. 5. How the solution can be sustainable (i.e. supportability) 6. Clearly identify other specific DoD or governmental customers who want to use the solution 

PHASE III: "The Primary goal of SBIR is Phase III. The contractor will pursue commercialization of the various technologies developed in Phase II for transitioning expanded mission capability to a broad range of potential government and civilian users and alternate mission applications. Direct access with end users and government customers will be provided with opportunities to receive Phase III awards for providing the government additional research & development, or direct procurement of products and services developed in coordination with the program. NOTES: a. Due to the large amount of expected interest in this topic, we will not be answering individual questions through e-mail, except in rare cases. Instead we will be holding a teleconference to address all questions in an efficient manner. This topic will be updated with the final call-in details as soon as the date is finalized. In the meantime, feel free to use the SITIS Q&A system. b. This SBIR is not awarding grants, but contracts, when registering in SAM.gov, be sure to select ‘YES’ to the question ‘Do you wish to bid on contracts?’ in order to be able to compete for this SBIR topic. If you are only registered to compete for grants, you will be ineligible for this topic. c. We are working to move fast, please register in SAMs and if already registered please double check your CAGE codes, company name, address information, DUNS numbers, ect. If they are not correct at time of submission, you will be ineligible for this topic. In order to ensure this, please include, in your 15-slide deck, a screenshot from SAM.gov as validation of your correct CAGE code, DUNS number and current business address along with the verification that you are registered to compete for All Contracts. d. Companies must be present at the Kessel Run Pitch event (July 2019 at the Kessel Run Software Factory located at 1 Beacon Street, Boston, MA) and complete their pitch to AF evaluators in order to receive an award. 

REFERENCES: 

1: "A Revolution in Acquisition and Product Support." Air Force Life Cycle Management Center, 2013, Retrieved 20 October from https://www.wpafb.af.mil/Portals/60/documents/lcmc/LCMC-Revolution-in-Acquisition.pdf?ver=2016-07-01-110338-350

2:  "Air Force Life Cycle Management Center Homepage," Retrieved October 20 from https://www.wpafb.af.mil/aflcmc/

3:  "The Heilmeier Catechism." DARPA, Retrieved October 24 from https://www.darpa.mil/work-with-us/heilmeier-catechism

KEYWORDS: Software, Development, Open-Source, SUAS, Sensor 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: This is a Pitch Day Topic, please see the above Pitch Day Topic instructions for further details. A Phase I award will be completed over 3 months with a maximum award of $75K and a Phase II may be awarded for a maximum period of 15 (or 27 month) and $750K. The objective of this topic is to explore innovative UAS and Counter-small UAS (C-sUAS) technologies that may not be covered by any other specific SBIR topic and thus to explore options for innovative solutions that may fall outside the Air Force’s current fields of focus but that may be useful to the US Air Force. This topic will reach companies that can complete a feasibility study and prototype validated concepts in accelerated Phase I and II schedules. This topic is specifically aimed at later stage development rather than earlier stage basic science and research. 

DESCRIPTION: This effort is a partnership between the Air Force Program Executive Office for Digital (PEO Digital), the Air Force Research Lab (AFRL), and the Tri-Service C-sUAS Swarm group. The Air Force PEO Digital is responsible for the acquisition of software and weapons systems including support for UAS air traffic avionics and control software, UAS applications to environmental sensing, and development of innovative C-sUAS technologies for defense of critical facilities. The AFRL leads the discovery, development and delivery of warfighting technologies for air, space and cyberspace forces including swarm autonomy and decision making, as well as open system approaches for UAS and subsystems like communications, human interfaces, and sensors , etc. The Air Force wishes to stay at the cutting edge of these technologies and seeks to partner with innovative small businesses that may have solutions to Air Force challenges. These are the high level challenge areas for which the Air Force is interested in novel solutions: 1. UAS payloads to defeat other UAS 2. UAS signature (optical, infrared, acoustic, radar, etc) identification software 3. UAS avionics open software trust and verification technologies 4. UAS sensing for weather hazard avoidance 5. UAS sensing for characterization of environmental conditions (wind, hydrology, RF spectrum, etc) 6. UAS sense and avoid technologies for operation in mixed manned/unmanned airspace 7. UAS applications to resilient PNT (mitigation of GPS degradation, etc) 8. Small UAS design assurance and airworthiness certification 9. Counter Swarm technologies 10. Agile technology insertion for UAS 11. Artificial intelligence and decentralized control for UAS swarms This topic is meant for innovative solutions to be adapted in innovative ways to meet DoD stakeholders’ needs in a short timeframe and at a low cost. 

PHASE I: "Validate the product-market fit between the proposed solution and a potential USAF stakeholder and define a clear and immediately actionable plan for running a trial with the proposed solution and the proposed AF customer. This feasibility study should directly address: 1. Clearly identify who the prime potential AF end user(s) is and articulate how they would use your solution(s) (i.e., the one who is most likely to an early adopter, first user, and initial transition partner). 2. Deeply explore the problem or benefit area(s) which are to be addressed by the solution(s) - specifically focusing on how this solution will impact the end user of the solution. 3. Define clear objectives and measurable key results for a potential trail of the proposed solution with the identified Air Force end user(s). 4. Clearly identify any additional specific stakeholders beyond the end user(s) who will be critical to the success of any potential trial. This includes, but is not limited to, program offices, contracting offices, finance offices, information security offices and environmental protection offices. 5. Describe the cost and feasibility of integration with current mission-specific products. 6. Describe if and how the demonstration can be used by other DoD or governmental customers. 7. Describe technology related development that is required to successfully field the solution. 8. Deliver an initial prototype or minimum viable product (MVP) code or product at the conclusion of the contract that can be adapted and/or matured to a more advanced stage during Phase II. The funds obligated on the resulting Phase I SBIR contracts are to be used for the sole purpose of conducting a thorough feasibility study using scientific experiments, laboratory studies, commercial research and interviews. Prototypes may be developed with SBIR funds during Phase I studies to better address the risks and potential payoffs in innovative technologies." 

PHASE II: "Develop, install, integrate and demonstrate a prototype system determined to be the most feasible solution during the Phase I feasibility study. This demonstration should focus specifically on: 1. Evaluating the proposed solution against the objectives and measurable key results as defined in the phase I feasibility study. 2. Describing in detail how the solution can be scaled to be adopted widely (i.e. how can it be modified for scale) 3. A clear transition path for the proposed solution that takes into account input from all affected stakeholders including but not limited to: end users, engineering, sustainment, contracting, finance, legal, and cyber security. 4. Specific details about how the solution can integrate with other current and potential future solutions. 5. How the solution can be sustainable (i.e. supportability) 6. Clearly identify other specific DoD or governmental customers who want to use the solution" 

PHASE III: "The Primary goal of SBIR is Phase III. The contractor will pursue commercialization of the various technologies developed in Phase II for transitioning expanded mission capability to a broad range of potential government and civilian users and alternate mission applications. Direct access with end users and government customers will be provided with opportunities to receive Phase III awards for providing the government additional research & development, or direct procurement of products and services developed in coordination with the program. NOTES: a. Due to the large amount of expected interest in this topic, we will not be answering individual questions through e-mail, except in rare cases. Instead we will be holding a teleconference to address all questions in an efficient manner. This topic will be updated with the final call-in details as soon as the date is finalized. In the meantime, feel free to use the SITIS Q&A system. b. This SBIR is not awarding grants, but contracts, when registering in SAM.gov, be sure to select ‘YES’ to the question ‘Do you wish to bid on contracts?’ in order to be able to compete for this SBIR topic. If you are only registered to compete for grants, you will be ineligible for this topic. c. We are working to move fast, please register in SAMs and if already registered please double check your CAGE codes, company name, address information, DUNS numbers, ect. If they are not correct at time of submission, you will be ineligible for this topic. In order to ensure this, please include, in your 15-slide deck, a screenshot from SAM.gov as validation of your correct CAGE code, DUNS number and current business address along with the verification that you are registered to compete for All Contracts. d. Companies must be present at the UAS Pitch event (17 July 2019 at Northeastern University’s Innovation Campus, Kostas Research Institute, in Burlington, MA) and complete their pitch to AF evaluators in order to receive an award. 

REFERENCES: 

1: "A Revolution in Acquisition and Product Support." Air Force Life Cycle Management Center, 2013, Retrieved 20 October from https://www.wpafb.af.mil/Portals/60/documents/lcmc/LCMC-Revolution-in-Acquisition.pdf?ver=2016-07-01-110338-350

2:  "Air Force Life Cycle Management Center Homepage," Retrieved October 20 from https://www.wpafb.af.mil/aflcmc/

3:  "The Heilmeier Catechism." DARPA, Retrieved October 24 from https://www.darpa.mil/work-with-us/heilmeier-catechism

4:  U.S. Air Force, Small Unmanned Aircraft Systems (SUAS) Flight Plan: 2016-2036, 30 Apr 2016.

KEYWORDS: Software, Development, Open-Source, SUAS, Sensor, Weather, Airworthiness, Spectrum 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: The objective of this SBIR is to develop, Test and Validate a standardized, compact, automated and easy-to-use shock tube capable of state-of-art measurements of the ignition-delay-time and fuel pyrolytic and oxidation histories (optical and/or otherwise). The fuel pyrolytic and oxidation intermediate species measured are those involved in key combustion reaction pathways for AF and other DOD propulsion systems, and their measurement enables characterization of fuel combustion chemistry and supports combustion model development efforts. 

DESCRIPTION: Fuel Combustion-chemistry properties determine molecular changes from high-energy-state fuel/oxidizer molecules to low-energy-state product molecules during the energy conversion process in AF and other DOD propulsion systems. Physically accurate and computationally efficient combustion chemistry models [1-3] are a critical part of physics-based modeling and simulation (M/S) tools for developing future generations of AF and other DOD propulsion systems such as solid/liquid rockets, aviation jet engines, and hypersonic scramjets. The capability of measuring fuel combustion chemistry properties such as the ignition delay and the fuel pyrolytic and oxidation intermediate species histories following key reaction pathways is a foundational element for the development and validation of such physically accurate and computationally efficient combustion chemistry models. Presently, the ignition delay and pyrolytic/oxidation species histories are mainly measured using shock-tubes equipped with start-of-art combustion diagnostic techniques (optical or intrusive probes) in research laboratories at leading universities. There are two long-lasting challenges: (1) non-standard facility/instruments and measurement procedures; and (2) expense in time and/or funding to operate such facilities. These shock-tube facilities and related combustion diagnostic instruments have been developed largely under incremental supports from AF (AFOSR) and other DOD 6.1 sources over the past several decades. Although the underlying scientific working principle has long been understood, due to the incremental nature of past development efforts in multiple universities by multiple agencies for different emphases, these facilities/instruments are of a research nature and not standardized, such that there are large variations in facility/instrumentation attributes. Comparing results from different facilities that use somewhat different procedures is often difficult. These facilities are usually expensive to operate, requiring long training times for graduate students or post-doc researchers to become proficient in facility and diagnostics operation. However, after many years of development, the shock-tube technology and associated combustion diagnostic techniques have matured sufficiently [4] to be standardized and transitioned for more applied uses (6.2 and beyond) at governmental research laboratories, such as AFRL, USAFA, or commercial aviation and aerospace industries, to support fuel characterization and fuel combustion-chemistry modeling. Furthermore, such standardized, compact and automated shock-tubes can be developed into a field deployable tool for fueling testing and quality control at fuel depots and major airports. This topic focuses on the transition of the state-of-art research shock-tube setup along with necessary combustion diagnostic techniques to standardized, compact and easy-to-operate instrumentation tools with maximum automation for the fuel characterization and combustion chemistry model development. Proposals must include the all following aspects in an integrated fashion and will be evaluated accordingly: (1) Capable of measuring ignition delay and pyrolytic and oxidation intermediate species histories of sufficient temporal resolution with acceptable uncertainty; (2) Flow initiation process: diaphragm-less systems are highly desired/preferred. The valve opening time and the impact of valve opening process on the shock-propagating flow must be quantified to be adequate for the measurements mentioned above. For any flow initiation approaches, full impacts of the flow initiation process on the shock propagation flow must be sufficiently quantified for making proper measurements mentioned above. (3) The boundary-layer and other non-ideal flow attributes: proposed designs much be able to provide an adequate one-dimensional shock-propagating core flow of sufficient size for the above mentioned measurements. Full impacts of the boundary layer and other non-ideal flow attributes must be sufficiently quantified. (4) Modular design and sufficient optical and probe accesses; and (5) Ease-of-use with maximum automation of operation and measurement processes suitable for laboratory technicians, without requiring highly-skilled research personnel. 

PHASE I: Efforts consist of the following: (a) review state of art shock-tube technologies and associated diagnostic techniques, their capabilities, limitations and uncertainties with respect to earlier stated measurement objectives; (b) propose a creditable design and creditable quantification approaches with sufficient scientific and technical substantiations to address the above elements (1)-(5). A Phase I proposal will not be considered without clearly describing such creditable quantification approaches of sufficient details based on scientific and technical logic, especially for items (2) and (3) stated above; (c) incorporation of needed diagnostic techniques (optical, probes, etc.); (d) formulating a test/validation plan for measuring ignition delay time and key pyrolytic and oxidation species histories for small molecular foundational fuels (CH4, C2H4, C3H8 etc.) and real AF/DOD fuels/fuel blends including but not limited to JP8/Jet-A/JP5, JP10 and RP-2/its derivatives. The proper execution of Items (a)-(d) forms the foundation of the Phase II proposal. Phase I efforts consist of the following: (a) review state of art shock-tube technologies and associated diagnostic techniques, their capabilities, limitations and uncertainties with respect to earlier stated measurement objectives; (b) propose a creditable design and creditable quantification approaches with sufficient scientific and technical substantiations to address the above elements (1)-(5). A Phase I proposal will not be considered without clearly describing such creditable quantification approaches of sufficient details based on scientific and technical logic, especially for items (2) and (3) stated above; (c) incorporation of needed diagnostic techniques (optical, probes, etc.); (d) formulating a test/validation plan for measuring ignition delay time and key pyrolytic and oxidation species histories for small molecular foundational fuels (CH4, C2H4, C3H8 etc.) and real AF/DOD fuels/fuel blends including but not limited to JP8/Jet-A/JP5, JP10 and RP-2/its derivatives. The proper execution of Items (a)-(d) forms the foundation of the Phase II proposal. 

PHASE II: Efforts focus on development and construction of prototype shock-tube system with the required diagnostic tools based on the Phase I design, and the execution of the test and validation plan developed in Phase I. Prototype systems will be delivered to DOD and/or other federal government laboratories and Institutions for testing usage. 

PHASE III: Based on the inputs from the testing usage defined in Phase II, further improve the system capability and develop the system into field deployable systems for fueling testing and quality control at fuel depots and major airports. 

REFERENCES: 

1. Sayak Banerjee, Rei Tangko, David A. Sheen, Hai Wang, C. Tom Bowman, An experimental and kinetic modeling study of n-dodecane pyrolysis and oxidation, Combustion and Flame (2015) 1-19.; 2. Wang, H., Xu, R., Wang, K., Bowman, C. T., Hanson, R. K., Davidson, D. F., Brezinsky, K., Egolfopoulos, F. N. “A Physics-based approach to modeling real-fuel combustion chemistry. I. Evidence from experiments, and thermodynamic, chemical kinetic and statistical considerations,” Combustion and Flame 193, 502-519 (2018). DOI: 10.1016/j.combustflame.2018.03.019.; 3. Xu, R., Wang, K., Banerjee, S., Shao, J., Parise, T., Zhu, Y., Wang, S., Zhao, R., Lee, D. J., Movaghar, A., Han, X., Gao, Y., Lu, T., Brezinsky, K., Egolfopoulos, F. N., Davidson, D. F., Hanson, R. K., Bowman, C. T., Wang, H., A Physics-based approach to modeling real fuel combustion chemistry. II. Reaction models of jet and rocket fuels. Combustion and Flame 193, 520-537 (2018). DOI: 10.1016/j.combustflame.2018.03.021.; 4. Ronald Hanson and David Davidson, Recent advances in laser absorption and shock tube methods for studies of combustion chemistry, Progress in Energy and Combustion Science (2014) 44-1

KEYWORDS: Combustion Chemistry, Pyrolysis, Shock-tube, Ignition Delay, Pyrolytic Pathways, Aerospace Propulsion Systems 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Broadband in-situ characterization of mm-wave components in vacuum 

DESCRIPTION: Characterizing millimeter-wave electronic components in vacuum, such as slow-wave structures, antennas, amplifiers, and passive networks, is a crucial and largely unmet need, especially at affordable prices that would enable innovation in more laboratories. The established commercial approaches at lower frequencies use vector network analyzers; at frequencies well above 100 GHz, however, such instruments [1] are rare and prohibitively costly, and largely incompatible with vacuum equipment. Transmission and reflection measurements from 50 to 500 GHz in vacuum conditions would enable testing of emerging millimeter and sub-millimeter-wave systems for space and vacuum electronic applications. Generation and detection of mm-wave test signals within the vacuum chamber would avoid lossy and expensive mm-wave hermetic links to bulky test equipment. While basic network analysis is a starting point, further refinements could include probe stations to hold devices under test and software to control and evaluate the data from the instrument. The goal is a vacuum-compatible packaged mm-wave generation, detection, and probing platform for economical network analysis at mm-wave frequencies, up to and exceeding 500 GHz. For scalability, key manufacturing processes must be modified for wafer-scale processing compatibility. Potential customers include Air Force research and university laboratories, start-up companies working in millimeter-wave systems and components, and established wireless companies, which need to characterize antennas, active devices and passive networks at frequencies above 50 GHz. For example, the growth rate in 2020 for mm-wave amplifiers will exceed 10% given the explosive growth of 5G wireless systems using millimeter-waves. 

PHASE I: Fabricate vacuum-compatible mm-wave network analysis probe head and demonstrate mm-wave characterization at atmosphere. Show that achieving network analysis measurements from 50 to 500+ GHz is feasible, and that probe cabling can transition into vacuum. 

PHASE II: Fabricate vacuum feed-throughs for probe cabling, and test mm-wave probe characterization under vacuum. Further optimize signal generation and detection for higher frequencies. 

PHASE III: Demonstrate key technology process optimizations for mass-production capability. Develop ancillary control and drive circuitry to move from lab prototype to commercial product. 

REFERENCES: 

1. J. Hesler, Y. Duan, B. Foley, T. Crowe, “VDI - THz Vector Network Analyzer Development & Measurements”, Virginia Diodes Newsletter, March 2010.; 2. Y. Duan, J Hesler, “Modular VNA Extenders for Terahertz Frequencies.”, 20th International Symposium on Space Terahertz Technology, Charlottesville, 20-22 April 2009.; 3. T. Gaier, L. Samoska, C. Oleson, and G. Boll, "On-wafer testing of circuits through 220 GHz," in Ultrafast Electronics and Optoelectronics, J. Bowers and W. Knox, eds., Vol. 28 of OSA Trends in Optics and Photonics, Optical Society of America, 1999.; 4. L. Chen et al., "Terahertz Micromachined On-Wafer Probes: Repeatability and Reliability," in IEEE Transactions on Microwave Theory and Techniques, vol. 60, no. 9, pp. 2894-2902, Sept. 2012. M. Hrobak, M. Sterns, M. Schramm, W. Stein and L. Schmidt, "Desi

KEYWORDS: Vector Network Analysis, Mm-Wave Characterization, Mm-wave Probes, Vacuum Electronics 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop and demonstrate a low SWaP-C network of RF spectrum awareness monitors that are able to navigate within, sense, share, and collectively characterize the local RF environment. 

DESCRIPTION: Global positioning system (GPS) and Global Navigation Satellite System (GNSS) based receivers tasked to operate in urban areas do so in an increasingly densely populated RF environment. Due to the availability of low-power consumer-level jamming devices, and the complex reflection/attenuation nature of urban environments, the RF spectrum can vary widely both temporally and spatially. Recently, extremely low-cost digital video broadcast decoding devices containing the Realtek 2832U demodulator chip were found to allow access to raw inphase/quadrature (I/Q) 8-bit sample streams [1]. Capable of tuning ~50-1800 MHz, these sub-$20 USB dongles enable software receiver processing of significant portions of the radio-navigation bands. A real-time GPS navigation solution has been demonstrated using this minimal hardware [2].Utilizing an array of these sensing nodes will allow for a characterization of the local RF environment including localizing interference sources. Although each individual node captures and process only 2 MHz of spectrum [3] instantaneously, their low-cost and frequency agility, schemes of sweep patterns and/or multiple co-located nodes can be used to effectively cover large portions of spectrum. Spectrum snapshots (e.g. Fast Fourier Transform results or small amounts of raw signal samples) and location data can be conveyed to a master node in order to synthesize the RF environment characterization. In such a system, the various SatNav constellation band plans can be highlighted and selected for navigation based on sensed spectrum conditions. Both ground and airborne nodes should be considered for this effort. 

PHASE I: Study of algorithms and approaches that characterize the RF environments from distributed, frequency agile, narrow-band nodes. This includes determining types and amounts of data required to be transferred from multiple sensing nodes to a master node. Also required is a survey of RF propagation in urban areas to determine number of nodes required for situational awareness. 

PHASE II: Develop a test plan and demonstrate RF environment characterization using a constellation of prototype nodes in a dense, urban area. Localize several strong signal sources for which location truth can be determined. Deliver RF sensing solution including communication infrastructure to government. Document design and test results in a final report. 

PHASE III: Complete integration of receiving nodes and transmitting elements with custom circuit layouts. Ruggedize system, analyze power requirements, and determine suitable portable power sources. 

REFERENCES: 

1. http://spectrum.ieee.org/geek-life/hands-on/a-40-softwaredefined-radio; 2. C. Fernández-Prades, J. Arribas, P. Closas, Turning a Television Into a GNSS Receiver, Proceedings of ION-GNSS+ Conference, September 2013, Nashville, TN. (http://ion.org/gnss/abstracts.cfm?paperID=405); 3. http://sdr.osmocom.org/trac/wiki/rtl-sdr; 4. Sarang Thombre, M. Zahidul H. Bhuiyan, Patrik Eliardsson, Björn Gabrielsson, Michael Pattinson, Mark Dumville, Dimitrios Fryganiotis, Steve Hill, Venkatesh Manikundalam, Martin Pölöskey, Sanguk Lee, Laura Ruotsalainen, Stefan Söderholm, Heidi Kuusniemi

KEYWORDS: GPS, Software Radio, Spectrum Sensing, Situational Awareness 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Identify and research passive and active low size, weight, power, and cost AJ techniques, technologies, and/or algorithms that can be integrated with and meet the SWAP-C constraints of the projected MGUE Increment 2 handheld receiver. 

DESCRIPTION: Anti-jam (AJ) research for GPS User Equipment has primarily been focused on producing high-performance systems that are targeted for aircraft, ship, and missile platforms operating in highly stressed Electronic Warfare (EW) environments. Controlled Radiation Pattern Antennas (CRPAs), combined with antenna electronics, have evolved to provide very high anti-jam nulling capability and high-gain beam-steering. However, the SWAP-C of these high-end systems put this capability out of reach for many users including the dismounted soldier and ground vehicles using handheld receivers like DAGR and PLGR. This large user base requires a higher level of AJ protection than is currently provided by the receivers internal GPS signal acquisition and tracking implementations to meet mission objectives in in a highly contested EW environment. Previous techniques were explored to enhance handheld AJ protection, such as a two-element nulling antenna accessory that could be externally attached to the handheld receiver. However, the SWAP of some of these techniques made them operationally cumbersome from a user perspective or provided only a marginal increase in AJ protection. Under the MGUE Increment 1 program, several techniques were developed under the Resiliency and Software Assurance Modification (RSAM) effort to enhance AJ performance of MGUE Increment 1 receivers. While these techniques are expected to transition to the MGUE Increment 2 modernized GPS handheld receiver, they will not provide the full level of AJ protection for dismounted operations in the projected EW environment. The Increment 2 handheld receiver effort is currently in the requirements definition phase. The initial SWAP constraints for this receiver are 35 cubic inches volume, 450 grams weight, and 19 hours of continuous use without battery change. This SBIR will identify and evaluate the performance and implementation of low-SWAP-C AJ techniques, including mechanical, passive, active and or algorithmic techniques, that are compatible with the MGUE Increment 2 handheld receiver SWAP constraints. The objective is to increase the AJ protection by at least 20 dB over that currently projected for the receiver itself. AJ capability should be based on scenarios consisting of multiple mobile and stationary ground-based jammers in an urban environment. Emphasis should be placed on solutions that are achievable by receiver developers (such as the MGUE Increment 1 prime contractors). The primary goal is to provide a comparative evaluation of multiple techniques, including performance, size, weight, and power and operational suitability assessments and implementation cost and prototype a sub-set of promising techniques. Offerors are encouraged to work with MGUE Increment 1 prime contractors to help ensure applicability of their efforts and begin work towards technology transition. Offerors should clearly indicate in their proposals what government furnished property or information are required for effort success. 

PHASE I: Conduct a comprehensive comparative assessment of low SWAP-C AJ techniques that are compatible with the SWAP constraints of the projected MGUE Increment 2 handheld to include AJ effectiveness, operational suitability, and size, weight, power, and cost. 

PHASE II: Since a physical implementation of the handheld receiver does not currently exist, design and implement a brassboard or prototype for one or two of the most promising low SWAP-C techniques using, as examples, a SWAP-compatible physical mock-up of the projected receiver and/or COTS development boards implementing M-code acquisition and tracking algorithms. The Phase 2 effort should include ensuring compatibility with interface requirements currently specified for the Increment 2 handheld receiver. 

PHASE III: With an MGUE Increment 2 vendor, integrate the selected SWAP-C AJ techniques demonstrated in Phase II with an Inc2 handheld prototype. Demonstrate the capability to meet performance and SWaP-C requirements. Identify transition opportunities for civilian applications such as those performed by DHS. 

REFERENCES: 

1. Global Positioning Systems Directorate Technical Requirements Document, Military GPS User Equipment (MGUE), Modernized Handheld Receiver (Draft); 2. John L. Volakis, Andrew J. O’Brian, Chi-Chih Chen, “Small and Adaptive Antennas and Arrays for GNSS Applications”, Proceedings of the IEEE, Vol. 104, No. 6, June 2016; 3. Joseph Przjemski, Edmund Balboni, John Dowdle, “GPS Anti-jam Enhancement Techniques”, Proceedings of the 49th Annual Meeting of the Institute of Navigation (1993), Cambridge, MA, June 1993; 4. Steve Rounds, “Jamming Protection of GPS receivers – Part I: Receiver Enhancements”, GPS World, Vol. 15, January 2004

KEYWORDS: 1 Anti-Jam 2 MGUE Increment 2 3 GPS Modernized Handheld 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Identify, evaluate, and demonstrate techniques for receivers to use one or a small number of higher power M-code signals to substantially improve jamming tolerance, relative to that without the higher power signals. 

DESCRIPTION: Heterogeneous Power Exploitation (HPE) allows GPS receivers to more fully benefit from a small number, as few as one, of higher power signals when the others are lower power. HPE involves a combination of signal use logic (smartly selecting higher power signals for acquisition and tracking) as well as advanced signal processing techniques that use the more robust higher power signals to aid tracking of less robust, lower power signals. For the foreseeable future, the GPS constellation will provide a range of received M-code power levels. Even the mix of Block II satellites and early GPS III satellites will provide received M-code power levels varying by more than 12 dB, not accounting for variations in receive antenna gain. With regional military protection (RMP) or higher power hosted quasi M (QM)-signals, the variation in received signal power levels could approach 25 dB. Current receivers are not specified or tested to fully benefit from the higher power signals. Research and development is needed to identify and demonstrate practical and effective techniques for HPE. The objective should be receiver processing techniques and approaches that use one or a small number of higher power signals to substantially improve jamming tolerance, relative to that without the higher power signals. 

PHASE I: The first phase will focus on the identification of receiver-based techniques to exploit the HPE and initial performance evaluation. Candidate techniques can be identified via literature review and/or invented by the performers. Once identified these techniques will be initially evaluated (e.g. via software simulation) to quantify their relative performance improvident. Recommendations will be made as to which techniques should be implemented in hardware as part of Phase II. Approaches and techniques should provide trade-off analyses including performance gain versus implementation complexity (e.g. power, SLOC, etc.) 

PHASE II: The second phase will focus on selective implementation of the best techniques identified in Phase I. These should be implemented in a real-time GPS receiver to allow for hardware-in-the-loop (HITL) testing. Once implemented the performance of these techniques will be evaluated over a range of situations (GPS constellation power levels, user state, user dynamics, etc.) 

PHASE III: The third phase will transition the capability to contractors for potential implementation in military GPS User Equipment. In addition, this phase could explore the techniques for applicability to civilian signals (e.g. L1C/A, L1C, L2C, and L5) to improve signal performance in jamming conditions since 5-10 dB variation in gain of these signals can be expected from fixed-radiation pattern antenna receive antennas. 

REFERENCES: 

1. Spilker, J. J. Jr., “Vector Delay Lock Loop Tracking—Position Estimation,” Paper presented at the IEEE Communication Theory Workshop, FL, April 1993.; 2. US Patent Number US5398034A, “Vector delay lock loop processing of radiolocation transmitter signals” 1993-03-29; 3. Barker, B.C., Betz, J.W., Clark, J.E., et al, “Overview of the GPS M Code Signal” The MITRE Corporation accessed 11/2018 from https://www.mitre.org/publications/technical-papers/overview-of-the-gps-m-code-signal; 4. Jones, Michael, “The promises of M-Code and quantum,” GPS World 13 December 2017, accessed 11/2018 from https://www.gpsworld.com/the-promises-of-m-code-and-quantum/

KEYWORDS: Global Positioning System, M-Code, MGUE, Vector Delay Lock Loop 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop innovative wafer-scale antenna and front-end components for a multi-element receive phased array for future W-band SATCOM uplinks. 

DESCRIPTION: Future military SATCOM concepts include V-band (71-76 GHz) downlinks and W-band (81-86 GHz) uplinks to support next-generation high-data-rate communications systems. These systems will extend to new SATCOM frequency spectrums to address frequency crowding at lower frequencies. Additionally, currently demonstrated array front-end components at these frequencies have relatively low output power. Further, while single-point RF receivers with gimbaled antennas address a potential W-band receiver architecture, phased array architectures are also viable for these satellite communications concepts. This Phase I SBIR focuses on defining advanced architecture and performance goals for a communications W-band receive phased array, designing wafer-scale antenna and front-end components, and defining a proof-of-concept multi-element demonstration vehicle. At a minimum, the array components/functions should include multi-beam, multi-channel receiver. Due to high atmospheric propagation at these frequencies, ultra-low noise amplifier and low power consumption technology and should be considered. Further, ± 9 degree scanning angles and 0.1 degree 3-dB-beamwidths should be included in the phased array architecture definition. Operating environment goals include a temperature range of -40 degrees to +85 degrees Celsius. The selected solid-state technologies should also support reliable space operation and operation in radiation environments. Radiation hardening goals include greater than 1 Mrad total dose radiation tolerance. 

PHASE I: Definition of the W-band phased array receiver architecture and performance goals, definition of a multi-element demonstration vehicle, and the design of required antenna and front-end components. 

PHASE II: Development and demonstration of the wafer-scale antenna and front-end components, as well as the multi-element W-band receive phased array designed in Phase I. 

PHASE III: Links technologies under this effort will further benefit applications in nearby frequency bands. Military: Military millimeter-wave phased array applications include W-band satellite communications uplink electronics for future high-data-rate communications systems. Commercial: Commercial W-band phased array applications potentially include commercial satellite communications services and 5G backhaul communication . 

REFERENCES: 

1. Gabriel M. Rebeiz, et al, Millimeter-Wave Large-Scale Phased Arrays for 5G Systems, UCSD, 2015 IEEE.; 2. Sadia Afroz; Virginia Polytechnic Institute and State University; Kwang-Jin Koh; Virginia Polytechnic Institute and State University, Power-Efficient W-Band (92–98 GHz) Phased-Array Receive Element With Quadrature-Hybrid Based Passive Phase Interpolator, International Microwave Symposium 2017.; 3. S. Shahramian ; M. J. Holyoak ; Yves Baeyens, A 16-Element W-Band Phased-Array Transceiver Chipset With Flip-Chip PCB Integrated Antennas for Multi-Gigabit Wireless Data Links, IEEE Transactions on Microwave Theory and Techniques, 2018; 4. Kerim Kibaroglu ; Mustafa Sayginer ; Gabriel M. Rebeiz, A Scalable 64-Element 28GHz Phased-Array Transceiver with 50 dBm EIRP and 8–12 Gbps 5G Link at 300 Meters without any Calibration, 2018 IMS.

KEYWORDS: W-band, Low Noise Amplifier, Satellite Communications 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop dual-band, linear-efficient high power amplifiers for cost-effective, multi-platform satellite communication uplinks. 

DESCRIPTION: The Air Force is interested in developing a new generation of dual-band, linear-efficient high power amplifiers to replace airborne and ground platform amplifiers that singularly address either Ka-band or Q-band operation. This development complements a current dual-band Ka/Q-band low noise amplifier development for the space segment. The innovatively-designed, multi-band power amplifier is expected to have applicability to cost-effective, multi-platform SATCOM uplink transmitter applications. This includes future frequency hopping applications for airborne platform-based uplinks in advanced SATCOM concepts. The performance goal for the dual-band HPA is power gain optimized in the 29.0-31.0 GHz band, as well as 43.5-45.5 GHz frequency band, with suppressed gain at the interim frequencies. Potential millimeter-wave power amplifier approaches may include solid-state power amplifiers (SSPAs) or traveling wave tube amplifiers (TWTAs). At the subcomponent level, various solid-state transistor, power combiner, and traveling wave tube approaches are feasible towards the integrated SSPA or TWTA. The research conducted under this topic should address the dual-band Ka/Q-band performance goals of greater than 100-watt output power, greater than 30% power-added efficiency (PAE), a minimum of 30 dB power gain and an operating temperature range of -40° to + 80° Centigrade. In general, power amplifier efficiency translates to dc power consumption requirements for electronics, as well as additional hardware to address corresponding cooling requirements. Further, linear performance should, at a minimum, address QPSK and 8PSK operation. 

PHASE I: Design dual-band Ka/Q-band high power amplifiers consistent with the performance goals and objectives identified above. Perform additional validation of the designs through modeling and simulation. 

PHASE II: Fabrication of the Phase I-designed subcomponents and their assembly into integrated high power modules, either solid-state power amplifier or traveling wave tube amplifier prototype(s). Evaluation and characterization of the prototype(s) for all relevant performance parameters. 

PHASE III: Military: Military high power amplifier applications include Ka-band and Q-band communications uplink electronics for Wideband Global SATCOM (WGS) and Advanced Extremely High Frequency (AEHF) systems. Commercial: Commercial Ka/Q-band high power amplifier applications include ground/airborne electronics where millimeter-wave power sources are required. 

REFERENCES: 

1. G. Berlocher, SSPA versus TWTA: Is There Room for Both?, Via Satellite, October 2014.; 2. J. Browne, TWTAs Power Satcom Systems, Microwaves and RF, April 2012.; 3. N. Escalera, et al., Ka-Band 30 Watts Solid State Power Amplifier, Microwave Symposium Digest, 2000 IEEE MTT-S International, pp. TUIF-42:561-563, 2000.; 4. X. Yu et al., "A Milimeter Wave 11W GaN MMIC Power Amplifier", Proc. Asia-Pacific Conf. on Antennas and Propagation (APCAP), pp. 1342-1344, 2014.

KEYWORDS: Traveling Wave Tube Amplifier, Solid-State Power Amplifier, Satellite Communications, Ka-band, Q-band 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop innovative wafer-scale antenna and front-end components for a multi-element transmit phased array for future high-power V-band SATCOM downlinks. 

DESCRIPTION: Future military SATCOM concepts include V-band (71-76 GHz) downlinks and W-band (81-86 GHz) uplinks to support next-generation high-data-rate communications systems. These systems will extend to new SATCOM frequency spectrums to address frequency crowding at lower frequencies. Additionally, currently demonstrated array front-end components at V-band have relatively low output power. Further, while single-point RF power sources with gimbaled antennas address a potential V-band transmitter architecture, phased array architectures are also viable for these satellite communications concepts. This Phase I SBIR focuses on defining advanced architecture and performance goals for a communications V-band downlink transmit phased array, designing wafer-scale antenna and front-end components, and defining a proof-of-concept multi-element demonstration vehicle. At a minimum, the array components/functions should include power amplification and beam steering. Due to high atmospheric propagation at these frequencies, EIRP >100 watts and per element power output >400 mW should be considered. However, thermal management feasibility should be evaluated. Further, ± 9 degree scanning angles and 0.1 degree 3-dB-beamwidths should be included in the phased array architecture definition. Operating environment goals include a temperature range of -40 degrees to +85 degrees Celsius. The selected solid-state technologies should also support reliable space operation and operation in radiation environments. Radiation hardening goals include greater than 1 Mrad total dose radiation tolerance. 

PHASE I: Definition of the V-band phased array architecture and performance goals, definition of a multi-element demonstration vehicle, and the design of required antenna and front-end components. 

PHASE II: Development and demonstration of the wafer-scale antenna and front-end components, as well as the multi-element V-band transmit phased array designed in Phase I. 

PHASE III: Military: Military millimeter-wave phased array applications include V-band satellite communications downlink electronics for future high-data-rate communications systems. Commercial: Commercial V-band phased array applications potentially include commercial satellite communications services. Technologies under this effort will further benefit applications in nearby frequency bands. 

REFERENCES: 

1. S. Zihir, et al., A 60 GHz 64-element Phased-Array Beam-Pointing Communication System for 5G 100 Meter Links up to 2 Gbps, 2016 IEEE MTT-S International Microwave Symposium.; 2. K. Tsukashima, et al., An E-band 1 W-class PHEMT Power Amplifier MMIC, Microwave Integrated Circuits Conference Digest, 2015 10th European Microwave Integrated Circuits Conference.; 3. A. Brown, et al., High Power, High Efficiency E-Band GaN Amplifier MMICs, Wireless Information and Systems Digest, 2012 IEEE International Conference on Wireless Information Technology and Systems.; 4. . Shahramian ; M. J. Holyoak ; Yves Baeyens, A 16-Element W-Band Phased-Array Transceiver Chipset With Flip-Chip PCB Integrated Antennas for Multi-Gigabit Wireless Data Links, IEEE Transactions on Microwave Theory and Techniques, 2018

KEYWORDS: E-band, V-band, Phased Arrays, Satellite Communications 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Development of compact, lightweight high-power solid-state power amplifiers for V-band crosslinks. 

DESCRIPTION: Compact 59-65 GHz crosslink solid-state power amplifiers (SSPAs) are required to meet future millimeter-wave satellite communications transmit power requirements. Today’s high-power-density technologies offer significant output power increases over currently-fielded solid-state device technologies and solutions. These device technologies, coupled with innovative power combining, are expected to provide unmatched millimeter-wave power performance in compact form factors, providing increased transmit power and range benefits without increasing satellite size and weight requirements. Potential approaches for linear-efficient V-band solid-state power performance should address both the high-performance millimeter-wave transistor, innovative circuit approaches, and compact low-loss power combiner approaches. The SSPA’s performance goals include simultaneous >50-watt output power, >30 dB power gain with gain variation less than ±1 dB, and >25% power-added efficiency performance across 59-65 GHz. The SSPA’s AM-to-PM performance should reflect <5 degrees/dB through 50-watt output operation. Additional goals include an operating temperature range of -40 degrees to +85 degrees Celsius. The selected solid-state power amplifier approach should support reliable space operation and operation in radiation environments. Radiation hardening goals include greater than 1 Mrad total dose radiation tolerance. 

PHASE I: Concept design and circuit simulations of the linear-efficient 59-65 GHz microwave monolithic integrated circuit (MMIC) power amplifier based on a suitable, high-performance millimeter-wave transistor process, as well as the integrated design of the power-combined SSPA. 

PHASE II: Fabrication of the linear-efficient prototype power amplifiers (MMICs, power combiner, integrated SSPA) according to the Phase I design. Characterization of the MMICs, combiner and SSPA for linearity, output power, and efficiency under typical signal and environmental conditions. 

PHASE III: Military: Military high power amplifier applications include V-band satellite communications crosslink electronics for systems such as Advanced EHF. Commercial: Commercial V-band high power amplifier applications include ground/airborne/space electronics where millimeter-wave power sources are required. Technologies and methodologies under this effort will further benefit commercial communication networks in nearby frequency bands. 

REFERENCES: 

1. K. Tsukashima, et al., An E-band 1 W-class PHEMT Power Amplifier MMIC, Microwave Integrated Circuits Conference Digest, 2015 10th European Microwave Integrated Circuits Conference.; 2. A. Brown, et al., High Power, High Efficiency E-Band GaN Amplifier MMICs, Wireless Information and Systems Digest, 2012 IEEE International Conference on Wireless Information Technology and Systems.; 3. J. Cheron et al., "High-Efficiency Power Amplifier MMICs in 100 nm GaN Technology at Ka-Band frequencies", Proc. Eur. Microw. Integ. Circuits Conf. (EuMIC), pp. 492-495, 2013.; 4. C.F. Campbell et al., "High Efficiency Ka-Band Power Amplifier MMICs Fabricated with a 0.15 um GaN on SiC HEMT Process", IEEE MTT-S Int. Dig., pp. 1-3, Jun. 2012.

KEYWORDS: V-band Crosslinks, Solid-state Power Amplifier, Power-added Efficiency, Satellite Communications 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a high spectral resolution longwave infrared hyperspectral sensor suitable for low-to-medium altitude airborne intelligence, surveillance, and reconnaissance. 

DESCRIPTION: Airborne hyperspectral imaging (HSI) sensors have demonstrated utility for material detection and identification. Additionally, longwave infrared (LWIR) HSI systems can operate day/night and can be used to monitor gaseous effluents as many gases possess strong spectral features within the 7-14um spectral range. Existing dispersive systems demonstrate excellent radiometric performance but are generally limited in spectral resolution due to the relatively small format of available focal plane array (FPA) technology [1]. Fourier transform infrared (FTIR) systems can achieve high spectral resolution but at the expense of added collection time. For airborne platforms, this added time places too much demand on pointing and stabilization to prevent spectral artifacts. As next generation very longwave infrared (VLWIR) FPAs with small pitch, large format, and extended spectral range become available [2], next generation LWIR HSI sensors can potentially be developed capable of collecting with high spectral resolution while maintaining sufficient radiometric performance and collection time. This effort will produce a high spectral resolution LWIR HSI sensor with >400 (T) (500 (O)) bands over a spectral range of 8.0-12.5um (T) (8.0-13.0um (O)) with <12nm (T) (<10nm (O)) spectral resolution measured as full-width half max (FWHM). Additionally, the sensor must be able to collect a spatial scene of >400x400 pixels in <2s while maintaining a noise-equivalent spectral radiance (NESR) of < 2uW/(cm2-sr-um) (T) (< 1uW/(cm2-sr-um) (O)), while viewing a 300K blackbody source. Optical distortions, such as smile and keystone, will be maintained to <1/8 of a channel. 

PHASE I: This effort will develop candidate designs and evaluate available FPA technology. A full system model will be developed to determine expected performance of the system in terms of spectral sampling, spectral resolution (full-width half max), smile, keystone, and NESR for expected frame rate and exposure time of the system. 

PHASE II: The effort will refine the design as needed, procure materials and equipment, and build the system. The system will be fully characterized in a laboratory to measure spectral resolution, spectral smile, keystone, and spectral NESR. Additionally, tower testing of the instrument will occur with relevant field targets to demonstrate imaging performance and spectral exploitation. Government equipment and labs may be used in support of system testing and characterization. 

PHASE III: Phase 3 will refine the design based on outcomes of tests and customer feedback in Phase 2. The system will be flight tested and further integrated into a relevant pod given customer interest. 

REFERENCES: 

1. J. Hall, et al, “Mako airborne thermal infrared imaging spectrometer – performance update,” Proc. SPIE, 9976, 997604-1 – 997604-9, (2016); 2. H. Figgemeier, et al, “State of the Art of AIM LWIR and VLWIR MCT 2D Focal Plane Detector Arrays for Higher Operating Temperatures,” Proc. SPIE, 9819, 98191C-1 – 98191C-16, (2016)

KEYWORDS: Longwave Infrared, Hyperspectral Imaging, Sensor 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Design, fabricate, and test small format GMAPD arrays for multifunction LiDAR cameras operating in direct detection and coherent sensing applications supporting Global Precision Attach (GPA) or Globally Integrated Intelligence Surveillance and Reconnaissance (GIISR) mission types. The arrays will operate at a 2 um wavelength, capable of operating without sizable cooing requirements with a goal of room temperature operation. 

DESCRIPTION: Recent advances in semiconductor development for Geiger mode avalanche photodiode (GMAPD) light detection and ranging (LiDAR) readout integrated circuits (ROIC) have provided means to reduce effective area of an individual pixel through improvements in detection circuit design and smaller semiconductor design rules. Typical SWIR detector designs for imaging LiDAR sensors operate below 1.7 um wavelengths, except for few designs which incorporate cryogenic cooling in order to maintain detection sensitivity. This topic seeks to develop small pitch, large format detector arrays capable of operating at a 2 um wavelength, with LiDAR functionality, without the need for physically sizable cooling. Thermoelectric cooling may be implemented for temperature control, with a goal of > 250 °K operating temperatures. Detector development should include physics-based modeling of the device structure in order to determine performance expectations and to aid in camera component development. Iterative design experiments are expected in order to yield insight into device physics. The detector arrays should be of a 32 x 32 format and scalable to larger formats, arrays with pixel pitch of 100 um with additional arrays of 50 um pitch and scalable to smaller pixel pitch, electrical connection at the pixel level with a metal pad on the APD, common anode or common cathode connections along 2 sides of the array, capable of operation at < 5 V above breakdown, capable of conducting pixel current while minimizing crosstalk and other noise effects across the array, and maximizing effective quantum efficiency. Laboratory testing of the detector arrays will be necessary in order to determine sensitivity and noise performance, and characterization of arrays’ performance is required. The detector arrays may be bonded to existing ROICs in order to fabricate laboratory-class LiDAR receivers, and provide a path toward fabrication of large format LiDAR receivers. Bonding of the detector arrays to fanout test fixtures and characterization of the detectors is desired. The following are design goals for a full receiver: LiDAR functionality, detection wavelength between 2.0 to 2.1 um, single photon detection, low dark count rate, operability of > 99%, nominal probability of detection (PDE) of ≥ 25% at a corresponding dark count rate of < 100 kHz with goal of < 10 kHz, uniformity of PDE and DCR across the array, sample bin interval of less than 1.5 nsec for direct detection modes, minimal quench and rearm duration supporting asynchronous operation in Geiger mode, and the ability to operate without cryo-cooling. The goal of the effort is to develop detectors for a Geiger mode LiDAR system which would provide data to generate 3-D point clouds and other data products. Detector cooling and power requirements can drive CSWaP of a full camera. Cooling, size, weight, and power (CSWaP) for the receiver would need to be considered for the final design, where insertion into a small UAV, existing targeting pod, or turret as a goal. Government furnished equipment is not required for this project. 

PHASE I: Develop design ideas for detectors, APD arrays, laboratory test configurations, and test plans for characterization of the devices. Develop a program plan, SOW, and performance expectations for the small format receiver in Phase II. Develop a commercialization plan. 

PHASE II: Design, fabricate, test and characterize small (32x32) format detector arrays incorporating 100 um pitch and 50 um pitch detectors. Provide laboratory test results, details of test methods. Deliverables include small format detector arrays with supporting electronics for laboratory testing. Develop a program plan, SOW, and performance expectations for a LiDAR receiver capable of insertion into SUAV’s, targeting pod, or turret. 

PHASE III: Design, develop, and test a LiDAR receiver capable of flight testing in an airborne laboratory type environment. Develop a program plan to integrate into an aerial platform and perform flight testing. Work with a system integrator to integrate into surrogate test platform, and perform flight demonstrations. 

REFERENCES: 

1. E. Duerr, et. al., “Antimonide-based Geiger-mode Avalanche Photodiodes for SWIR and MWIR Photon-counting”, Proc. SPIE 7681, Advanced Photon Counting Techniques IV, 76810Q (28 April 2010; 2. J. Campbell, “Recent Advances in Avalanche Photodiodes”, IEEE Journal of Lightwave Technology Vol. 34, 6 July 2015; 3. Mark A. Itzler ; Mark Entwistle ; Mark Owens ; Ketan Patel ; Xudong Jiang ; Krystyna Slomkowski ; Sabbir Rangwala ; Peter F. Zalud ; Tom Senko ; John Tower ; Joseph Ferraro; Design and performance of single photon APD focal plane arrays for 3-D LADAR imaging. Proc. SPIE 7780, Detectors and Imaging Devices: Infrared, Focal Plane, Single Photon, 77801M (August 17, 2010); 4. R. Sidhu, L. Zhang, N. Tan, N. Duan, J.C. Campbell, A.L. Holmes, Jr., C.-F. Hsu and M.A. Itzler, “2.4 lm cutoff wavelength avalanche photodiode on InP substrate”, IEEE Electronics Letters Vol. 42, 2 Feb. 2006

KEYWORDS: LADAR, LiDAR, APD, Geiger Mode Lidar 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop conformal optical steering system for a LADAR sensor suitable for scaling via tiling small sub-apertures to realize larger, meter class apertures with low size, weight, and power. This device should be amenable for steering the field of view (FOV) of a high-resolution LADAR imaging receiver. 

DESCRIPTION: The Air Force has pressing requirements for operating in contested environments where intelligence, surveillance, and reconnaissance (ISR) assets cannot operate freely. The Air Force requires high confidence ID for high value targets to protect air crews and to establish air superiority. Two approaches considered are deployment of large aperture sensors, such as LADAR, to provide stand-off imaging capability, and use of attritable, unmanned aerial systems (UAS) for penetrating ISR and strike. Both approaches need enhanced target ID capabilities of LADAR as well as persistent passive imaging via mid-wave or long-wave imaging for cueing and situational awareness. Conventional optical systems rely on gimbaled optics, which significantly limit the aperture size and increase Cost, Size, Weight and Power (C-SWAP). For large apertures, the pod cannot physically accommodate the gimbal size required and a conformal approach is the only way forward. The attritable platform has tight C-SWAP restrictions, which imposes severe performance trades for gimbaled approaches. Non-mechanical beam steering (NMBS) is a technology that provides the ability to direct a laser beam without physical movement of the optical elements. NMBS offers performance advantages over mechanical systems with reduced weight, random access to steering directions, expanded field of view (FOV), and higher steering speeds. In addition NMBS offers logistical advantages, with electronic optical calibration, high precision and accuracy, and sealed long life components. NMBS devices have been developed that steer to discrete points at high efficiency using a stack of polarization gratings, or addressable points with a single optical phased array (OPA). The goal of this effort is to demonstrate a conformal optical steering system that steers 2 micron light. The steering system should use smaller sub-apertures with a well-defined optical phase relation between them to create larger effective apertures. This technique is meant to create an essentially scalable fabrication method for realizing arbitrarily larger effective apertures up to at least 6 inches diameter with a goal of up to 12 inches diameter. For example, the use of nanophotonic optical elements, or metasurfaces, for creating engineered optical properties of light has been shown to be a versatile technique for beam shaping, but methods for scaling this to larger apertures remains a challenge. This and other approaches for beam steering or shaping will be considered, with an emphasis on techniques which can be readily scaled to larger sizes through repeated patterning of smaller sub-apertures. The final steering system should be capable of steering to >(+/-)15 degrees in one dimension, (goal (+/-)30 degrees), with >80% power in steered beam. Devices should operate at >200Hz, with a goal of 1 kHz operation. Commercial application of a conformal low C-SWAP optical steering would have similar benefits for civil uses of LADAR mapping. Government materials, equipment, data or facilities are not necessary. 

PHASE I: In this initial phase, device concepts will be developed, evaluated, and computer modeled. Design challenges and trade-offs will be tabulated and areas in need of additional R&D will be identified. Critical factors to consider are, maximum theoretical transmission, aperture size, low SWAP packaging, and demonstrating that the technology can achieve requirements through models. SWaP guidelines to consider include the potential for aperture sizes from 6 inches up to about 40 inches in diameter, weight under 5 kilograms, and average power usage under 10 W. Preliminary designs should be developed for Phase II. 

PHASE II: Devices will be constructed and tested for beam steering efficiency, aperture, and SWAP requirements. Tests will be conducted to verify performance parameters of the device with a short-wave infrared camera surrogate for a LADAR. Iteration on designs and improvements will be made as the production process is refined and preliminary designs for a Phase III device should be made. 

PHASE III: A flight ready version of the design will be built, steering efficiencies, and size, weight and power of both device and control system in form factor for integration in a UAS. Current manufacturing process will be evaluated and refined to improve yield while reducing cost. 

REFERENCES: 

1. Optical Phased Array Technology, Paul F. McManamon et. al., Proceedings of the IEEE, Vol. 84, No. 2, February 1996.; 2. High-Efficiency All-Dielectric Metasurfaces for Ultracompact Beam Manipulation in Transmission Mode, Mikhail I. Shalaev et. al., Nano Letters, 15 (9), pp 6261–6266 (2015); 3. Large area metalenses: design, characterization, and mass manufacturing, Alan She et. al., Optics Express Vol. 26, No. 2 pp. 1573-1585, (2018); 4. Wide-Angle, Nonmechanical Beam Steering Using Thin Liquid Crystal Polarization Gratings, Jihwan Kim et. al., Advanced Wavefront Control: Methods, Devices, and Applications VI, Proc. of SPIE, Vol. 7093, 709302, (2008).

KEYWORDS: NMBS, LIDAR, LADAR, Non-mechanical, Steering, Beam Steering, Optical, Conformal, Sub-aperture, Metasurfaces 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop next generation cognitive and fully autonomous sensor technologies amenable to a highly distributed airborne swarm 

DESCRIPTION: The global proliferation of advanced integrated defense system technologies continues to present a major challenge. It is recognized across the DoD that a distributed swarm platform architecture is needed. Major advances in commercial technologies i.e. embedded computing with integrated neuromorphic engine, software defined radios, and radar system on a chip, there is a major challenge in putting all this together. The goal of this research is to develop CFAST amenable technologies. Emphasis is on solutions that are low size, weight, power and cost. All physical sensor modalities will be considered. The focus of this research is the sensor payload, packaging, and platform integration, not on communications or networking. 

PHASE I: Develop a fully integrated conceptual design for CFAST technologies. A basic feasibility analysis using modeling and simulation to establish a new sensor approach. 

PHASE II: Further refine and prototype the CFAST design. The output should be a design that is ready to enter into a Phase III 

PHASE III: DUAL USE APPLICATION: The proposer will identify potential commercial and dual use applications such as low SWAP-C sensors and embedded computing that include cognition engines. 

REFERENCES: 

1. L. O. Spencer, "US Air Force Key to Third Offset Strategy," in Defense News, ed, 2016.; 2. Airborne Swarms. Available: https://www.darpa.mil/news-events/2017-04-23; 3. Small form factor embedded computing. Available: https://en.wikichip.org/wiki/apple/ax/a11; 4. R. Guerci and E. J. Baranoski, "Knowledge-aided adaptive radar at DARPA: an overview," Signal Processing Magazine, IEEE, vol. 23, pp. 41-50, 2006.

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop techniques for radar resource allocation for closed-loop radar detection and tracking 

DESCRIPTION: Onerous challenges imposed by an A2AD environment call for closed loop radar operation for concurrent detection and tracking of targets from single and distributed radar systems. In the context of the sense-learn-adapt framework or perception-action framework, this necessitates the use of past data to determine future radar illumination and data collection. Current techniques do not optimally and automatically balance the need to detect, track, and identify targets. Recently, cognitive radar approaches have been used to compute sensing actions that are expected to maximize the utility of the received data. Similarly, past efforts on information-theoretic sensor management have produced a framework for managing the resources of an agile sensor, where the utility of the sensing action is judged by the expected amount of information flow. This effort solicits the development of intelligent sensor management approaches for optimized sensing in a dynamic, complicated environment characterized as containing many moving targets, performing maneuvers that are intermittently obscured to the sensor. While previous efforts have focused on portions of this problem, this topic seeks approaches that address using multiple sensors for detection, and tracking of multiple targets from single and distributed radar in a closed loop manner. Specifically, we seek approaches to capture the scene probabilistically and use this information to drive future sensing actions, and lead to quantitative improvements in performance over current approaches as measured by standard tracking benchmarks such as time until correct detection and identification, track mean square error, and optimal sub-pattern assignment (OSPA). Ideally, we seek radar resource allocation techniques that incur a weak dependence on the number of sensors and the number of targets. The approach must afford application of ideas from cognitive sensing to guide agile sensor action at the next time step and beyond, such as selection of pointing, mode, waveform and PRF. 

PHASE I: Develop a closed loop sensor management framework for concurrent detection, and tracking of ground targets in a single sensor setting. A host of multi-objective optimization problems encountered in this context, need to be addressed. Performance analysis and benchmarking of the approach are called for using standard measures. 

PHASE II: Extend the approach to include distributed radars tracking multiple targets. Validation of the concepts need to be done via simulation and experimentation. 

PHASE III: Techniques from this effort will be fundamental to the performance evaluation and benchmarking of closed loop radar detection and tracking. Technology insertion opportunities include platforms such as AWACS and Global Hawk. 

REFERENCES: 

1. 1. S. Haykin, Y. Xue, and P. Setoodeh, “Cognitive Radar: Step Toward Bridging the Gap Between Neuroscience and Engineering”, The Proceedings of the IEEE, vol. 100, no. 11, pp. 3102-3130, Nov. 2012.; 2. D. Fuhrmann, “Active-Testing Surveillance Systems, or, Playing Twenty Questions with Radar”, in Proc. 11th Annual Adaptive Sensor and Array Processing (ASAP) Workshop, MIT Lincoln Laboratory, Lexington, MA, Mar. 11-13, 2003.; 3. C. Kreucher, A. Hero, K. Kastella, and M. Morelande, “An Information-Based Approach to Sensor Management in Large Dynamic Networks”, The Proceedings of the IEEE, vol. 95, no. 5, pp. 978-999, 2007.; 4. S. Liu, S. Bhat, J. Zhang, Q. Ding, R. Narayanan, A. Papandreou-Suppappola, S. Kay, and M. Rangaswamy, “Design and Performance of an Integrated Waveform-Agile Multi-Modal Track-before-Detect Sensing System”, 2011 Asilomar Conference on Signals, Systems

KEYWORDS: Closed Loop Radar, Resource Allocation, Distributed Radar 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop advanced hyperspectral exploitation algorithms incorporating 3D spatial information for improved target detection and identification. 

DESCRIPTION: Hyperspectral imaging (HSI) has demonstrated utility for material classification and target detection/identification. Generally, hyperspectral exploitation algorithms operate using spectral information alone due to insufficient spatial resolution of the sensor or the lack of coincident data from another sensing modality, such as RADAR, LIDAR, or passive 3D imaging. False alarms and low detection/ID confidence can exist for certain target classes that are not well separated using spectral information alone. As sensor technology matures, more opportunities exist to collect HSI data with coincident 3D spatial information at each pixel of the HSI data cube. This information could come from LIDAR data collected over the same spatial area or with novel passive sensing modalities, such as passive 3D HSI [1]. This additional information can be used to help improve the separability of material and target classes, thereby reducing false alarms and improving ID confidence. Previous efforts in exploiting HSI with coincident LIDAR data have demonstrated benefits for material classification [2]. This effort seeks to improve and expand upon previous work with emphasis specifically on target detection and identification rather than material classification. Research should focus not only on the use of 3D spatial target information but implications for atmospheric characterization, shadow mitigation, bi-directional reflectance distribution function (BRDF) properties, and other items associated with the physics of radiative transfer. Assumptions that can be made regarding this effort include: 1) sensor viewing geometry is known along with solar geometry, 2) targets will span multiple pixels, 3) a spectral library of target and background signatures exists, 4) knowledge exists about the 3D structure of the targets of interest in the sense that the target shape is known (i.e. vehicle shape/size, etc.), 5) hyperspectral data will be in calibrated spectral radiance units, and 6) 3D spatial information available for each hyperspectral pixel with in the form of point cloud data and/or co-registered digital surface model data at roughly ½ the ground sample distance of the HSI data. Algorithms should produce a confidence measure associated with each target ID. Algorithms should demonstrate an order of magnitude decrease in false alarms with a 25% increase in ID confidence when compared with state-of-the-art spectral-only algorithms currently being used by the Air Force. Algorithms should be able to operate near real-time (within seconds or minutes of data collection) or a path demonstrated to optimize for near real-time operation using state-of-the-art processing hardware, such as graphical processing units (GPUs). 

PHASE I: It will explore and develop novel algorithms and test with synthetic data if appropriate. Testing will continue using government furnished airborne hyperspectral data and coupled 3D point-cloud data. Algorithm performance will be quantified and compared with current state-of-the-art spectral-only detection and ID algorithms. 

PHASE II: It will modify and further develop the algorithms based upon Phase 1 results. Further testing will occur using additional government-furnished data sets. The code will additionally be optimized with a hardware architecture identified for real-time or near real-time implementation. 

PHASE III: It will transition the software for incorporation into existing hyperspectral exploitation tools or other assets based upon interaction with the customer. 

REFERENCES: 

1. J. Ahlberg, et al, “Three-dimensional hyperspectral imaging technique,” Proc. SPIE, 10198, 1019805-1 – 1019805-10, (2017); 2. M. Khodadadzadeh, et al, “Fusion of Hyperspectral and LiDAR Remote Sensing Data Using Multiple Feature Learning,” IEEE JSTARS, Vol. 8, No. 6, (2015)

KEYWORDS: Target Detection, Identification, Hyperspectral Imaging, 3D Fusion 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop compact payload capable of collecting high spatial resolution thermal imagery and wide area longwave infrared (LWIR) hyperspectral imagery (HSI) to fit within the constraints of a 5" gimbal for use with SUAS platforms. 

DESCRIPTION: The Air Force has a need to perform ISR in contested environments. Group I and II SUAS (i.e., those under 55 lbs) are potential enablers for such missions due to their low cost and low probability of detection. However, they lack sensors for nighttime, automated passive detection/ID over large areas, particularly for difficult targets like those hidden by camouflage, concealment, or deception. ISR using longwave infrared (LWIR) hyperspectral imaging (HSI) systems has demonstrated utility in those challenging scenarios, but existing systems are too large and do not meet the size, weight, power (SWaP) constraints imposed by SUAS. This topic seeks development of uncooled LWIR HSI systems or development of novel compact cooled systems to be integrated with a broadband thermal imaging system (either MWIR or LWIR) to fit within the SWaP constraints of a 5” gimbal and corresponding SUAS. This effort will provide a 5” diameter gimbal suitable for a Common Launch Tube-deployed SUAS of less than 50lbs operating at a typical slant range of 1500ft and altitude of 200 feet and higher. The gimbal shall provide broadband NIIRS-6-quality (T) (NIIRS-7 or better (O)) thermal infrared (TIR) imagery (either MWIR or LWIR) with LWIR hyperspectral measurements collected across a broader field-of-view (FOV) with nominally 1.5m (T) ground sample distance (GSD, 1.0m (O)). The LWIR HSI system shall cover a spectral range of 7.5-11um (T) (7.5-13.5um (O)) with adequate spectral resolution, quantified as the full-width half-max (FWHM) of the system spectral response function (SRF), and sensitivity, quantified as noise-equivalent spectral radiance (NESR), to detect a range of military targets for which signatures will be provided. Note, due to the SWaP constraints, solutions may require novel uncooled LWIR systems [2] or scanned point spectrometers using cooled linear detector arrays. The system shall provide on-board processing resources (FPGA, GPU) for integration of gov’t provided algorithms for tracking and/or hyperspectral target detection/ID (T). The gimbal broadband TIR imagery shall be visually lossless after transmission (T). The transmitted chip/frame rate shall be 0.25 hertz (T), 2 hertz (O). Ground coverage of the TIR imagery shall be sufficient to fully encompass the rear aspect of a vehicle, 10x10 feet (T) (20 x 20 feet (O)) at range. The LWIR HSI shall meet an area coverage rate of 5000m2/s (T) (20,000 m2/s (O)). The FOVs shall be operator-steerable over a large part of a lower hemisphere field of regard (T). This effort will not develop entirely new gimbal structures, but will develop a payload, and processing capability. An off-the-shelf gimbal or mature prototype is the expected starting point. This gimbal shall support typical SUAS maneuvering and fly-ins, and shall compensate for disturbances due to gusts and air turbulence. The gimbal should provide accurate line-of-sight pointing data, on-gimbal inertial measurement, and interface to platform GPS (T). 

PHASE I: Identify the hardware requirements for a NIIRS-6-capable 5” TIR gimbal with spectrometer covering the LWIR portion of the spectrum, including stabilization, optics, and focal plane array. Conduct a Systems Requirement Review (SRR). Prepare a preliminary design of the gimbal and payload and hold a preliminary design review (PDR). Use modeling and simulation to justify performance. 

PHASE II: Perform detailed design of the gimbal and payload. Conduct Critical Design Review. Continue modeling and simulation to improve system performance. Based on these results, build a prototype 5” gimbal and payload or breadboard system if budget does not permit full gimbal integration. Evaluate system performance in laboratory and tower (T), and flight test (O) environments. It shall not be assumed that the government will furnish the gimbal for payload integration. However, government facilities and equipment may be used in support of lab and/or tower testing. 

PHASE III: Refine design based on outcomes of tests and customer feedback in Phase II; develop a manufacturing plan and/or select a partner for production of 5” gimbals. 

REFERENCES: 

1. Air Force Unmanned Aerial System (UAS) Flight Plan 2009-2047, http://archive.defense.gov/DODCMSShare/briefingslide/339/090723-D-6570C-001.pdf; 2. P. Lucey, et al, “A compact Fourier transform imaging spectrometer employing a variable gap Fabry-Perot interferometer,” Proc. SPIE, 9101, (2014)

KEYWORDS: SUAS; Imaging; NIIRS, Hyperspectral, Thermal, Longwave; Gimbal 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop EO/IR-specific state of the art machine learning method(s) for improving utility of ISR sensor products to provide enhanced interpretability and extend range performance over visual image assessments. 

DESCRIPTION: The Sensors Directorate of the Air Force Research Laboratory (AFRL/RY) and AF Life Cycle Management Center have been partnering on sensor technology research and development for ISR applications covering a range of passive and active EO/IR sensor concepts. Relevant research has the potential to support the DoD in manned and unmanned airframes. For this topic, the research should focus on the capability of performing National Image Interpretability Rating Scale (NIIRS) 5 or better level tasks on NIIRS 4 imagery where the images acquired are degraded due to low signal to noise ratio, atmospheric conditions, etc. These tasks are to be performed on passive single band imagery. The rapid expansion of research in the areas of state of the art machine learning, artificial intelligence, and deep learning open the possibility of improved image interpretability at a given imaging range, as well as the potential for further extending range performance of EO/IR sensor systems. One major challenge is acquiring or accurately modeling datasets for training and learning. Acquired datasets would have to be labeled after the collection to aid with training and learning. Collection of training and learning data will be provided by the offeror, no government facilities, equipment, etc. will be provided. An additional, but related, challenge is that training data may only be collected over a pristine or limited set of conditions. It is important to understand how training datasets and machine learning transfers to other data collection ranges, environmental conditions, and even target variations. This area of research is known as transfer learning. Performance metrics will focus on accomplishing NIIRS 5 or better tasks on NIIRS 4 imagery with 75% accuracy as a threshold and 100% accuracy as an objective. 

PHASE I: Research will focus on: 1) identifying and securing suitable datasets and/or modeling tools for providing data to train state of the art machine learning methods; 2) baselining a set of machine learning tools, including those methods required for feature extraction (including deep learning approaches), & transfer learning; and 3) providing an initial performance assessment, recommending next steps in refining state of the art machine learning tools. 

PHASE II: Research will focus on refining machine learning tools based upon Phase I recommendations. Additionally, the contractor will secure, generate, or collect more relevant training data. The contractor will perform a final assessment of the machine learning tools, including assessing potential performance gains over visual image analyses and testing limitations of transfer learning methods. The contractor will deliver all developed tools, algorithms, and data to the government. The contractor will initiate discussions with sensor system developers, exploitation processing developers, and other avenues for transition of machine learning techniques. 

PHASE III: This phase will match the Phase II machine learning tools with appropriate applications and pursue systems developers to refine and transition the tools for the specific system(s). The primary candidates include both existing operational and planned future DoD reconnaissance imaging systems, as well as commercial remote sensing systems for civil applications, such as mining and crop/forest health. The focus will be on refining tools that can be applied to detect, recognize, identify, and recommend actions in remote sensing performed by EO/IR sensors. 

REFERENCES: 

1. Zhang, Liangpei, Lefei Zhang, and Bo Du. "Deep learning for remote sensing data: A technical tutorial on the state of the art." IEEE Geoscience and Remote Sensing Magazine 4.2 (2016): 22-40.; 2. Paxman, R. G., Rogne, T. J., Sickmiller, B. A., LeMaster, D. A., Miller, J. J., & Vollweiler, C. G. (2016). Spatial stabilization of deep-turbulence-induced anisoplanatic blur. Optics express, 24(25), 29109-29125.; 3. Ball, J. E., Anderson, D. T., & Chan, C. S. (2017). Comprehensive survey of deep learning in remote sensing: theories, tools, and challenges for the community. Journal of Applied Remote Sensing, 11(4), 042609.; 4. Marcum, R. A., Davis, C. H., Scott, G. J., & Nivin, T. W. (2017). Rapid broad area search and detection of Chinese surface-to-air missile sites using deep convolutional neural networks. Journal of Applied Remote Sensing, 11(4), 042614.

KEYWORDS: Remote Sensing; High-resolution Imaging; Multispectral; Hyperspectral; Deep Learning; Convolutional Neural Networks; Object Detection; Target Recognition; Imaging Through Turbulent Media; Image Reconstruction-restoration; Hyperspectral; Big Data; Computer 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop high-resolution rapid refresh weather forecasts (Nowcasts) in support of real-time battle management (RPA, dynamic taskings, etc.) in data-sparse locations 

DESCRIPTION: There have been a number of breatkthroughs in the public and private sector utilizing traditional data sources to gather weather data to develop a short-term rapid update weather model. The Air Force has a large number of non-traditional data sources that could be used to gather and feed a large swath of previously unavailable weather data into the AFW Enterprise and forecasting systems. These unique AF & DoD non-traditional data sources, such as OPIR (Overhead Persistent Infrared), should be explored for use in local data assimilation to improve model performance for support of high-resolution rapid-refresh-like "Nowcast" capabilities. This would aid in weather support to time-sensitive operations in limited domains, such as remotely piloted aircraft and Chemical, Biological, Radiological and Nuclear (CBRN) events occurring in down-range operations. 

PHASE I: Conduct an analysis to identify any likely non-traditional data sources (available and near-term), such as OPIR, within the AF/DoD from which weather data could be gathered but has not been, historically. 

PHASE II: Based upon the research in Phase I, develop an algorithm or data analysis technique to extract environmental information from the non-traditional data sources and integrate it with AFW model data into a Nowcast system. 

PHASE III: Expanding upon work from Phase II, identify and develop means to integrate and present Nowcast information to users through the AFW Enterprise system. Identify and address any gaps between the proposed solution and the AF requirements. 

REFERENCES: 

1. Air Force Weather Operations Roadmap (November 2017), HQ USAF/A3W, Washington, DC; 2. Rapid Refresh (RAP) NOAA Hourly Assimilation/Modeling System at Earth System Research Laboratory: https://rapidrefresh.noaa.gov/; 3. Sun et al, 2014: Use of NWP for nowcasting convective precipitation. Bull. Am Met. Soc., 2014, 409-426. https://journals.ametsoc.org/doi/pdf/10.1175/BAMS-D-11-00263.1; 4. Browning, K.A., 1982: Nowcasting. Academic Press, London, 256 pp.

KEYWORDS: Weather Forecasting Technology, Nowcasting, High Resolution Numerical Weather Prediction, OPIR, 4 Dimensional Data Assimilation, Rapid Update Cycles 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop detector technology that can drive Energetic Charged Particle sensor SWaP below current State of the Art by 6x or more while simplifying design and adding multi-phenomenology detection capability. 

DESCRIPTION: While current Energetic Charged Particle (ECP) sensors are acceptable for large space systems (~4kg, 10W, 3600cc) [1] and a second generation is being developed with 2x to 4x reduction in SwAP, further reduction in SWaP and system cost and complexity while retaining the full sensor capability [2] is desired for future systems using a variety of dedicated, contributing, and hosted platforms, ranging in size from current large vehicles to cubesats. As even second generation ECP sensors are large compared to some of these platforms, further reduction in SWaP is desired, but the minimum sensing capability remains a requirement. The intent is to develop detector technology that can be shown to drive down not just detector SWaP, but overall system SWaP by a factor of 6x or more over existing designs while adding phenomenology detected by reducing detector size, simplifying the electronics required to acquire the data, and limiting the need for high voltage, low-noise electronics, on-board data processing, etc. While [2] lists the energy range desired, some relief may be granted on energy range if dramatic SWaP reductions can be demonstrated while otherwise meeting requirements. As an example, utilizing solid-state detectors to avoid the need for higher-SWaP approaches to spectroscopy for energies below 1keV is an attractive option, even if it is unlikely to achieve the absolute lowest energy range required. The design should be able to be shown to function within the extreme space environment that is desired to be measured and not be susceptible to contamination from photons, other particle species, or different energies of the desired particle measurement. Additionally, detection of phenomena beyond energetic particles is desirable to support broader space situational awareness (SSA) needs, including other natural and man-made effects [i.e. 3]. Addition of detected phenomenology could lead to improved awareness for the host vehicle, and reduce the overall system SWaP. Additional capability to discriminate other threat and hazard phenomenology is strongly desired, but the detector must be able to properly characterize both the ECP environment and the additional phenomenology as hazardous or benign simultaneously, within desired accuracies. 

PHASE I: Evaluate proposed detector technology via modeling and simulation, limited prototyping, and conceptual design studies to evaluate suitability for ECP and other detection missions while achieving SWaP reductions. 

PHASE II: Refine detector technology. Develop and test breadboard detector/sensor mockup to show SWaP gains and test detector against laboratory representations of the charged particle environment and other phenomenologies. 

PHASE III: Develop demonstration sensor system suitable for insertion into ECP sensors and/or other detector technologies. Support demonstration of multi-phenomenology detection on test flight or in assorted high-fidelity laboratory environments. If suitably capable, this technology should find broad uptake throughout national security space and potentially for commercial and civil customers as well. 

REFERENCES: 

1. Lindstrom, C “The Compact Environmental Anomaly Sensor Risk Reduction (CEASE-RR): A Pathfinder for Operational Energetic Charged Particle Sensors” IEEE Nuclear and Space Radiation Effects Conference, 17-21 July 2017, New Orleans, LA; 2. Wheelock, A. “White Paper on ECP Energy Range and Flux Requirements” [[WILL PROVIDE AS ATTACHMENT TO SITIS ENTRY]]; 3. Stephani, K. A., et al. (2014), Analysis and observation of spacecraft plume/ionosphere interactions during maneuvers of the space shuttle, J. Geophys. Res. Space Physics, 119, 7636–7648, doi:10.1002/2013JA019476.

KEYWORDS: Spacecraft, Anomaly, Attribution, Energetic Charged Particle, Threat Warning 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop non-destructive evaluation techniques to image and analyze defects and non-uniformities in Li-ion batteries, and correlate those to a failure mechanism of the cell. 

DESCRIPTION: Undetected defects and non-uniformities in Li-ion cells can impact a spacecraft’s mission assurance, causing costly integration and launch delays or even catastrophic mission failure. These defects can originate from the manufacturing process or form during cycling or transportation. Non-destructive evaluation and analysis of Li-ion cells can prevent defective or degraded cells from impacting mission assurance. Common non-destructive evaluation techniques for internal imaging of Li-ion cells and batteries are computed tomography (CT) X-ray imaging, magnetic resonance imaging (MRI), and thermography. Poor contrast, excessive image noise, low spatial resolution, and artifacts contribute to poor image quality with these techniques, and can prohibit proper flaw identification and resolution of fine features. Beyond defect identification, analysis of defect type and impact on performance is also critical for mission assurance. This solicitation aims to improve non-destructive evaluation and analysis techniques for enhanced understanding of internal defects and their correlation to cell failure mode. Examples of defects include foreign object debris, non-uniformities, and other manufacturing defects, such as wrinkles or tears within an electrode stack or jellyroll, and within free space in the Li-ion cell. Some examples of defects formed during cycling and transportation are dendrite growth and gas pocket formation. These undesirable Li-ion cell flaws can result in increased self-discharge, internal shorts, and degraded cell performance. Methods proposed under this solicitation must demonstrate detection, identification, and analysis of undesirable manufacturing defects and hazardous cell evolutions. Non-destructive techniques and methods with spatial resolution comparable with the onset of dendritic growth are of interest. Techniques should present a method to differentiate features of interest from artifacts. Analysis should consider defect type, size, and effect on cell performance, to include failure mode. Analysis techniques can be software related or other. Techniques should be non-intrusive and provide timely data without impact to manufacturing operations. Research techniques that would be prohibitive or inappropriate in a manufacturing environment are not the focus of this solicitation. Advancements to non-destructive techniques and analysis mentioned above and novel techniques not described in this solicitation will be considered. 

PHASE I: Perform preliminary analysis of NDE technique in a laboratory setting. Determine critical defect size, resolution, and limitations of imaging technique. Correlate defect type to cell failure mode. 

PHASE II: Demonstrate NDE technique in a manufacturing setting. Relate defect type, size, and location to degradation or failure mechanism of cell with accompanying software and/or database. Demonstrate high-throughput process with minimal effect on manufacturing time and process. 

PHASE III: Validation testing of proposed non-destructive technique and analysis with minimal impact to operations in a manufacturing setting. 

REFERENCES: 

1. D.P. Finegan, et al., Investigating lithium-ion battery materials during overcharge-induced thermal runaway: an operando and multi-scale X-ray CT study, Physical Chemistry Chemical Physics, Royal Society of Chemistry 18, 30912-30919 (2016).; 2. Shearing, P.R., et al., Multi Length Scale Microstructural Investigations of a Commercially Available Li-ion Battery Electrode, J. Electrochem. Soc 159, A1023-A1027 (2012).; 3. Romanenko, K., et al., New opportunities for quantitative and time efficient 3D MRI of liquid and solid electrochemical cell components: Sectoral Fast Spin Echo and SPRITE, J. Magnetic Resonance 248, 96-104 (2014).; 4. Robinson, J.B., et al., Detection of Internal Defects in Lithium-ion Batteries Using Lock In Thermography, ECS Electrochem. Lett. 4, A106-A109 (2015).

KEYWORDS: Non-destructive Evaluation, Li-ion, Defects, Mission Assurance 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop sensor solutions that can be embedded into printed structures and aid in the qualification of Additive Manufacturing (AM) components for launch and space vehicles. 

DESCRIPTION: The world of manufacturing is changing rapidly, with products being designed, made, and used in new ways as a result of AM. Processes used to manufacture critical components for launch and space vehicle component applications must still be formally qualified. While efforts are underway to tackle the process, alternative methods call for embedded sensors to be integrated into parts during the printing process.. These sensors are envisioned to be utilized for qualifying the part during and after production, but may also be useful after production for assessing component integrity during fielded use. Various sensing methodologies are of interest including but not limited to purely passive components such as strain gauges, thermistors, etc. as well as active solutions that utilize powered components to generate elastic waves or characterize structural responses like piezo-electrics. Sensors can be read via wired approaches by taking leads to test points on the external surface of the part, however, more advanced methods are of interest that incorporate wireless methods for data and power as well as suit materials that are metallic or dielectric. Furthermore, it is ideal if the sensor can be printed along with the part rather than be a separate component that is embedded requiring process halting for manned labor, but this is not a requirement. While no one technology is expected that an address all stated needs, this list is intended to define the scope of interest. 

PHASE I: Develop sensing method and evaluate effectiveness for characterizing print relevant defects and assess integration/embedding methodologies and impact of insertion on overall print quality. Demonstrate by analysis and/or test the feasibility of such concepts and that the approach be utilized for qualification of a representative part. 

PHASE II: Demonstrate the technology developed in Phase I. Tasks shall include, but are not limited to, a demonstration of embedded functionality, limitations of approach in a larger setup. 

PHASE III: Utilize the process developed during phase II and implement the approach on prototype launch vehicle or spacecraft hardware. Develop an approach and means to transition the technology to the user community including industry, academia, and government. 

REFERENCES: 

1. Macdonald, et.al., Multiprocess 3D printing for increasing component functionality, Science , Vol. 353, Issue 6307 , 30 Sep 2016.; 2. Seifi, et al., “Overview of Materials Qualification Needs for Metal Additive Manufacturing,” Journal of Materials, March 2016, Volume 68, Issue 3, pp 747–764; 3. “A Summary Review of Wireless Sensors and Sensor Networks for Structural Health Monitoring,” The Shock and Vibration Digest 2006.; 4. EELV New Entrant Certification Manufacturing and Quality audits, SpaceX, 2014-15

KEYWORDS: Additive Manufacturing, 3d Printing, Qualification, Sensors, Wireless, Inspection, Verification, Validation, Launch Vehicle, Space Vehicle, Satellite 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a high-conductance, device attach thermal interface material (TIM) for use in high power density applications such as the interface between a GaN Power Amplifier and heat spreader or carrier. 

DESCRIPTION: Current thermal management of solid state power amplifiers (SSPAs) in space is limited in its ability to spread power densities from the channels of active Power Amplifier devices (PA) to the large area thermal radiators required for ultimate rejection of heat to space. Current power densities at the bottom of the PA device can exceed 62 W/cm2 and are expected to climb to values >1488 W/cm2 in the next 5-6 years. At these expected power densities, it is apparent that current state of the art solders used at this interface will no longer be acceptable due to the need for higher performance. The Device Attachment TIM shall provide a heat transfer coefficient >1340 W/cm2-C over an area of 0.3 cm x 0.3 cm. The TIM shall provide sufficient attachment with high thermal performance to survive various environments it will be subjected to through the satellite mission, including dynamic loads, large diurnal variations, and thermal cycles. The high thermal conductance is required in a space environment (vacuum and no gravity), as well as on Earth in any orientation with respect to gravity for ground testability. The TIM shall meet performance over an operating temperature range of 0°C to 150°C and must survive a temperature range of -60°C to 150°C. Please be sure to address the thermal induced stress on the heat spreader after thermal cycles in a specific application as this will vary depending on the mission. In addition, the TIM shall not require significant cure time or any harsh processing environments that would damage the device, unit or system (including temperatures over 250 °C). The TIM shall be free of potential workmanship issues to avoid (or at least limit) the thermal vacuum testing required for recurring, standard designs. Proposers are highly encouraged to team with systems integrators and payload providers to ensure applicability of their efforts and to provide a clear transition path. 

PHASE I: Develop concepts to provide a robust, reliable TIM that has the potential to provide a heat transfer coefficient >1340 W/cm2-C. Demonstrate by analysis and/or test the feasibility of such concepts to meet all requirements stated above. 

PHASE II: Optimize and fully demonstrate a TIM capable of providing an effective heat transfer coefficient >1340 W/cm2-C. Perform thermal performance testing and thermal cycling to confirm all above requirements have been met under both on-orbit and ground test environments to verify susceptibility of debonds at large temperature variations and power densities. Perform testing on a large number of samples to verify robustness and that the TIM is independent of workmanship issues. 

PHASE III: This research would benefit all military and commercial satellite programs, including MILSATCOM and global positioning satellite programs. TIMs are required for all high power electronic components used on aerospace systems. 

REFERENCES: 

1. Gilmore, D. G., Spacecraft Thermal Control Handbook Volume I: Fundamental Technologies, 2nd Ed, The Aerospace Press, El Segundo, CA, 2002.; 2. Liu, J., T. Wang, B. Carlberg, and M. Inoue, "Recent Progress of Thermal Interface Materials," ESTC (2008), 2nd, pp. 351-358, 1-4 Sept. 2008; 3. Hansson, J., Ye, L., Rhedin, H., Liu, J., “A Review of Recent Progress of Thermal Interface Materials: From Research to Industrial Applications,” IMAPS Nordic Annual Conference 2016 Proceedings, June 5-7, 2016.; 4. "Spacecraft Thermal Control Workshop Proceedings," Aerospace Corporation, March 20-22, 2018 (available directly from Aerospace Corporation at stcw.mailbox@aero.org)

KEYWORDS: 1 Thermal Management 2 GaN Power Amplifier 3 Thermal Interface 4 High Power 5 Solder 6 Die Attach 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop a laboratory benchtop-sized charged particle accelerator suitable for supporting calibrations and characterizations of Energetic Charged Particle (ECP) sensors without resorting to licensed radioactive sources and/or large accelerator facilities. 

DESCRIPTION: The Air Force has mandated Energetic Charged Particle (ECP) sensors on all future Air Force satellites. In order for these sensors to accurately measure the space environment, calibration is usually required. For charged particle detector calibrations, the current norm is to use a limited number of accelerator facilities that are large, expensive, and heavily subscribed. Additionally, many facilities are sufficiently old that they may have unexpected down time for maintenance. In addition, the facilities are largely optimized for either medical or radiation effects testing. The typical alternative is to use licensed radioactive sources, which can emit particles at high enough energies to simulate the space environment. However, these radioactive sources emit a spectrum of energies, making true calibration challenging. In addition, radioisotopes that emit high energy protons do not exist. A benchtop- or rackmount-sized, spectrally pure charged particle accelerator as a calibration source would allow for ECP vendors to perform their own calibrations of sensors without licensed radioactive sources and the need for expensive and hard-to-schedule beam time at larger accelerator facilities. The objective of this topic is to develop a laboratory benchtop calibration source that can provide a narrow, spectrally-pure, beam for calibration of ECP sensors. These sources would accelerate electrons from 10 (far term goal) to 50 (near term goal) keV at the lowest energies up to 2 (near term goal) to 5 (far term goal) MeV at the highest energies and/or protons (highly desired) from 1 MeV up to 10 (near term goal) to 100 (far term goal) MeV with a beam energy full width half max of less than 25% (near term goal) or 10% (far term goal). It is desired that the accelerator can be tuned over a range of energies up to its maximum. Unlike much of the current focus in tabletop accelerator research, the desired particle flux needs to be relatively low and ideally adjustable: 1 particle/cm^2/s to 10^6 particles/cm^2/s. It is desired that this low particle flux is ideally retained throughout the entire accelerator so that radiation protection requirements can be kept to a minimum. Methods of limiting the maximum produced particle flux are also highly desired to prevent damage to equipment under test as well as reducing radiation protection requirements. The particle flux produced needs to be as close as possible to an unbunched, continuous source as most existing space particle sensors experience pile-up/dead-time when inter-particle arrival times at the sensor approach 1 µs. Finally, the source beam is desired to be as uniform as possible across at least a 1” beam spot. (SSA TN 952) 

PHASE I: Initial design and modeling of system performance. Perform risk-reduction prototyping of key components leading to demonstration of accelerator behavior. 

PHASE II: Prototype bench accelerator capable of demonstrating all key technologies and identifying necessary additional technology improvements required to meet goals. Demonstrate beam energy tuning capability and document system operation. 

PHASE III: Develop and document final product suitable for straightforward laboratory use and further commercialization. 

REFERENCES: 

1. R. J. England, et al., “Dielectric laser accelerators”, Rev. Mod. Phys., vol. 86, pp. 1337–1389 (2014).; 2. Esarey, E. Schroeder, C. B. & Leemans, W. P. Physics of laser-driven plasma-based electron accelerators. Rev. Mod. Phys. 81, 1229–1285 (2009).; 3. Seidl, P.A. et al. Demonstration of a compact linear accelerator. arXiv:1802.00173 [physics.acc-ph] 1 Feb 2018.; 4. V. Smirnov, S. Vorozhtsov, and J. Vincent, “Design Study of an Ultra-Compact Superconducting Cyclotron”, Nucl. Instr. Meth. vol. 763, pp. 6–12, 2014.

KEYWORDS: Calibration, Accelerator, Charged Particle, Miniaturization 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Development of a prototype hyperspectral microwave sensor which significantly increases the bandwidth and line channel spatial wavenumber density of space-based passively-measured microwave radiances emitted and transmitted through the earth's atmosphere. The anticipated products of the prototype hyperspectral microwave sensor include improved accuracy and diagnosis and prediction of 3-D radiative transfer through optically-thick clouds which can assist missile launch plume detection in the presence of sunlit-clouds. 

DESCRIPTION: Modern passive microwave space-borne sensors have a limited number of channels available, totaling between 5 and 30 channels. This limited number of channels has been shown to be insufficient to solve for the ill-posed nature of the inversion of the geophysical state from space-borne measurements. This is especially true for cases where cloud, rain and/or ice are present in the atmosphere. In this case, a large uncertainty exists due the lack of knowledge about the particle density, shape, size distribution, vertical structure, and temperature dependence. A larger number of channels will help solve for the inherent ambiguities in these cases. This will also provide (1) a higher vertical resolution for the temperature and humidity sounding in all-weather conditions, (2) a better distinction between the surface and the atmospheric signals leading to retrievals of ocean wind vectors, snow and ice, soil moisture, (3) better surface typing due to the different spectral signatures associated with the different surface parameters mixtures, and (4) a better characterization of the microwave spectroscopic parameters (line width, line strength, line shape, frequency shift). While sensors operating in the infrared, short wave infrared, and near-infrared have experienced an ever increasing number of channels and bands with the new hyperspectral sensors, microwave sensors -- despite their large proven benefits to numerical weather prediction and their ability to penetrate cloud and sense within and below the cloudy and rainy layers -- have not seen their number of channels increase, mainly due to technological challenges. This type of sensor would be expected to have significant positive impacts on the forecast skills of numerical weather prediction models due to the increase in sounding retrievals,, especially if deployed in space with large spatial and temporal coverages. This improvement is expected in medium-range weather forecasts as well as in the nowcasting/short-term forecasting of mesoscale events. Besides the large number of channels (between hundreds and thousands) sought, in a range between 6 GHz and 300 GHz, it is emphasized that the noise level should be as low as possible and at least as low as current state of the art sensors by taking advantage of the new developments in radiometry technology. 

PHASE I: Define what is meant by "hyperspectral microwave" in terms of frequency, wavenumber, and wavelength differentials, including the total number of channels. Develop a prototype hyperspectral microwave sensor design to include expected signal-to-noise ratio, radiance levels, channel or band spatial wave-number spacing, and applicable observing system simulation experiments (OSSE) in order to assess the impact of additional spectral channels and bandwidth on numerical weather prediction accuracy. 

PHASE II: Build a prototype hyperspectral microwave sensor based on the design approved in phase I employing the most recent technological advances as appropriate. Conduct phased sensor tests including on-ground, tower borne, and airborne tests. Refine data assimilation techniques for ingestion of the hyperspectral measurements into 3-D cloud forecast models such as those developed at the 557th Weather Wing. 

PHASE III: Apply the space-based hyperspectral microwave sensor towards military applications including 3-D global cloud diagnoses and forecasts, and surface snow and ice cover for ISR and Missile Warning. Civilian applications potentially include improved aviation weather hazard and in-flight forecasts and medium range weather prediction. 

REFERENCES: 

1. Blackwell, W.J., L.J. Bickmeier, R.V. Leslie, M.L. Pieper, J.E. Samra, C. Surussavadee, and C.A. Upham, 2011: Hyperspectral microwave atmospheric sounding. IEEE Transactions on Geoscience and Remote Sensing, 49, 128-142; 2. Townes, C.H., and A.L. Schawlow, 1975: Microwave Spectroscopy. Dover, New York, 699 pp.; 3. Rothman, L.S., et al, 2013: The HITRAN2012 molecular spectroscopic database. Journal of Quantitative Spectroscopy and Radiative Transfer, 130, 4-50.; 4. Liu, Q., and F. Weng, 2002: A microwave polarimetric two-stream radiative transfer model. Journal of the Atmospheric Sciences, 59, 2396-2402.

KEYWORDS: Molecular Spectroscopy, Emissivity, Polarization, Radiative Transfer, Transmission, Reflection, Absorption, Microwave Imagery, Microwave Soundings, Weighting Functions 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop large-area, low-cost, solar simulator capable of AM0 illumination of solar modules composed of multijunction solar cells with more than three subcells. 

DESCRIPTION: The 30% efficient InGaP/InGaAs/Ge triple junction solar cell has been considered state-of-practice among nearly all major government and commercial spacecraft for over a decade [1]. The U.S. Air Force (AF), in collaboration with the U.S. space solar cell industry, continues to drive improvements of multijunction solar cells to improve size, weight, and power (SWaP) metrics. Higher solar cell efficiency and novel array architectures provide mission enabling power levels and reduce system-level costs. To continue pushing the limits of SWaP metrics, new solar cell architectures are being developed, such as the inverted metamorphic multijuction (IMM) architecture [2]. Some of these designs contain more than three subcells and thus require new specialized characterization equipment. Accurate electrical characterization (e.g., current-voltage (I-V) measurements) of these new space solar cells require new tools such as multi-zone solar simulators that are capable of accurately simulating the AM0 spectrum and give the ability to tune the spectral intensity within certain spectral ranges [3]. In addition to testing at the cell level, panel-level integrators must use large-area solar simulators, such as a large-area pulsed solar simulator (LAPSS) [4], to characterize the output at the panel level. The measurements gained from using these tools give confidence in the electrical output at a high level of integration (i.e., including cells, interconnects, wiring, bypass/blocking diodes, etc.). In recent years, cell development has outpaced development of large-area simulators capable of testing panels that incorporate new, >3 subcell multijunction cell architectures. The Air Force is seeking to develop a large-area pulsed solar simulator capable of AM0 illumination of a 2m X 2m space solar array panel that contains solar cells with >3 subcells. The simulator should be capable of 2% areal uniformity and 2% temporal stability, allow for adjustable intensity, and be spectrally tunable to accommodate different solar cell architectures. . The pulse length should allow for a full I-V sweep or for a data point(s) to be taken per pulse so long as the panel can be adequately thermally controlled. The simulator developed under this program should be capable of satisfying the illumination requirements of the AIAA-S112 qualification for space solar array panels. Recently, LED based solar simulators have been used for characterizing CubeSat arrays [5] and show promise for large area applications. However, due to their relatively small illumination area, many LEDs must be used which adds complexity. These challenges may be overcome though with proper cooling and electrical integration and control. This call for proposals does not require a solution based on LEDs but would welcome potential ideas incorporating them. 

PHASE I: Develop large area solar simulator designs that enables characterization of large area (2m X 2m) space solar array panels under the AM0 spectrum. Perform preliminary testing and analysis of the identified options to support down select and Phase II development planning. 

PHASE II: Mature the most promising large area solar simulator design and perform required testing and analysis to determine the uniformity and stability of the electrical characterization at the panel level using the simulator as an illumination source. The goal is to have the technology matured to TRL 4 or higher at the end of the Phase II effort. 

PHASE III: Deliver full-scale AM0 solar simulator capable of illuminating 2m X 2m solar module with 2% areal uniformity and 2% temporal stability. The simulator should be capable of satisfying AIAA S-112 requirements. 

REFERENCES: 

1. King, R. R., et al. "Next-generation, high-efficiency III-V multijunction solar cells." Photovoltaic Specialists Conference, 2000. Conference Record of the Twenty-Eighth IEEE. IEEE, 2000.; 2. Pantha, Bed, Mark Stan, and Daniel Derkacs. "Inverted metamorphic multijunction solar cell." U.S. Patent Application No. 15/352,941.; 3. Montgomery, Kyle H., et al. "Characterization of a TS-Space quad-source solar simulator." Photovoltaic Specialists Conference (PVSC), 2012 38th IEEE. IEEE, 2012.; 4. Kruer, Mark A. "Large area pulsed solar simulator." U.S. Patent No. 5,984,484. 16 Nov. 1999.

KEYWORDS: High-efficiency, Solar Cell, Large Area Pulsed Solar Simulator, Inverted Metamorphic 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a Military GNSS Data Service that gathers GNSS ephemeris, clock, health, status, and other key information, ensures the trustworthiness of the data, and is capable of delivering data to military data networks. 

DESCRIPTION: *** The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 5.4.c.(8) of the solicitation and within the AF Component-specific instructions. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. Please direct questions to the AF SBIR/STTR Contracting Officer, Ms. Kristina Croake, kristina.croake@us.af.mil. * * * * * * * * * * * * * Traditionally, military users have relied on access to the navigation data message from the GPS signal in space to obtain current ephemeris, clock, satellite health, and other important data necessary for Positioning, Navigation, and Timing (PNT) from GPS. Due to the slow data rate of the Navigation Data Message (NDM) and an average age of data of 12 hours, the resiliency and performance of military receivers is actually, in some cases, worse than consumer devices. Billions of cell phones with inexpensive GPS chip sets benefit from Assisted GPS (A-GPS), which provides current ephemeris and timing data that enables rapid acquisition of the GPS signal and, in many cases, more accurate positioning and timing. No joint military A-GPS capability exists today. Typical Time-to-First-Fix (TTFF) requirements for military receivers are specified in tens of seconds or minutes, compared to less than 6 seconds for a typical A-GPS equipped cell phone. A key technical challenge is developing open data standards and interfacing with diverse DoD networks while providing a high degree of trust and resilience against cyberattacks. Additionally, as military users migrate to multi-GNSS, there is a need to provide near real-time notification of anomalies to users over available datalinks. The focus of this topic is developing a Military GNSS Data Service, drawing data from GPS and GNSS monitoring systems, suitable for integration with operational networks in an Area of Operations, that supports three enhancements to traditional satellite navigation. First, improved resiliency is obtained by assisted-GPS/GNSS data that improves initial synchronization performance. Second, enhanced accuracy is achieved by delivering Zero Age of Data (ZAOD) to the user, reducing the position and timing errors associated with satellite clock and ephemeris errors. Third, improved integrity is supported by providing users with near real-time notification of GPS or GNSS anomalies. Together, these capabilities provide a powerful enhancement to GPS and multi-GNSS use on the battlefield, leveraging existing tactical data links, and with little to no modification of military receivers. The primary goal of this effort is to develop the data service, including the architecture, protocols, interfaces, and information assurance features necessary to deliver trusted GNSS data to military users. Consideration should be given to extracting data from multiple monitoring sources such as the GPS control segment, National Geospatial-Intelligence Agency, the Jet Propulsion Laboratory, and other government and commercial sources. New monitoring stations are not within the scope of this topic, although leveraging new or emerging monitoring receiver and monitoring station initiatives is encouraged. The ultimate goal for a Military GNSS Data Service is a joint capability that services air, land, sea, space, and cyber domains. However, for this SBIR topic, demonstration of the capability for a single domain is acceptable, providing the solution is scalable to support diverse applications across all domains. 

PHASE I: Develop an architecture and preliminary design for a Military GNSS Data Service to support a single domain, with a plan for demonstrating the capability for a targeted application in Phase II. 

PHASE II: Implement and demonstrate a prototype Military GNSS Data Service for the targeted application, including GPS and Galileo data. The prototype should provide a real-time demonstration of the benefits of Military Assisted GNSS, including acquisition, accuracy, and integrity warning. 

PHASE III: Develop a Joint Military GNSS Data Service that supports multiple domains, and can be integrated into a theater command and control system. 

REFERENCES: 

1. Van Diggelen, Frank, A-GPS: Assisted GPS, GNSS, and SBAS. Boston: Artech House, 2009.; 2. Vallina-Rodriguez N., Crowcroft J., Finamore A., Grunenberger Y., Papagiannaki K. When Assistance Becomes Dependence: Characterizing the Costs and Inefficiencies of A-GPS. SIGMOBILE Mob. Comput. Commun. Rev. 2013;17:3–14.; 3. DoD CIO, “Department of Defense Information Technology Environment,” August 2016.; 4. Djuknic, George M., Richton, Robert E., “Geolocation and Assisted GPS”, Communications, February 2001, PP 123-125.

KEYWORDS: GNSS Data Service, A-GPS, Alternate-GPS 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Mature use of graphene in a Lithium-Ion Battery through the development of full cell configuration using pre-lithiated anodes. 

DESCRIPTION: Mass of spacecraft power system components can be a significant portion of the overall spacecraft mass. In order to reduce the mass required for spacecraft batteries and to meet exponentially increasing satellite energy requirements to support tomorrow’s warfighters, advanced energy storage cell development is required. Current Lithium-ion batteries use graphite as an anode. The use of graphene or graphene enhancements to replace graphite shows great promise in providing high gravimetric capacity while also maintaining reasonable cycling stability. Proposed technologies should be able to withstand 3-5 year operational lifetimes, maintain reasonable capacity (80%), and exhibit cycling stability after 20,000 cycles. Much research has been performed exploring graphene enhancements to energy storage cells. Review of the literature shows several different graphene and graphene enhanced anodes with 2x gravimetric potential compared to graphite and modest reduction in cycling capacity. Most research was performed in a half cell configuration which doesn't provide an accurate picture of energy and power density for operational cells. This topic aims to advance graphene electrodes and graphene enhancements to full cells for a space application. Approaches may include improvements to cell components, novel materials or processes, or other innovative ideas. However, production of full cells requires a pre-lithiation step to obtain decent electrochemical performances which increases difficulty in battery manufacturability. Producing a full cell, with a pre-lithiation step, is critical in assessing future graphene performance as an anode in battery use. 

PHASE I: Utilize existing research to determine viability and suitability of graphene anodes for future development into a full cell configuration. Perform initial testing and analysis of available graphene enhancements and anodes with chosen cathode(s) to down-select. Predict performance metrics (energy/power density, etc.) for chosen anode/cathode/electrolyte combinations. 

PHASE II: Of the downselected graphene or graphene enhanced anodes, perform a manufacturing study to determine which material types are optimal for prelithiation steps. Based on the results of the study, begin the process of creating a manufacturing method that simplifies the prelithiation stage and provides consistent pre-lithiation results. Execute the pre-lithiation stage and analyze the results. 

PHASE III: Manufacture the prelithiated anodes. Determine anode/cathode/electrolyte formulations for best performance and combine into full cells. Characterize the full cells for energy, power density and weight for potential space qualification. 

REFERENCES: 

1. Critical Insight into the Relentless Progression Toward Graphene and Graphene Containing Materials for Lithium Ion Battery Anodes https://onlinelibrary.wiley.com/doi/full/10.1002/adma.201603421; 2. Pre-Lithiation Strategies for Rechargeable Energy Storage Technologies: Concepts, Promises and Challenges https://www.mdpi.com/2313-0105/4/1/4/htm; 3. Current Progress of Si/Graphene Nanocomposites for Lithium-Ion Batteries https://www.mdpi.com/2311-5629/4/1/18/htm; 4. Characterization of a hybrid Li-ion anode system from pulsed laser deposited silicon on CVD-grown multilayer Graphene https://link.springer.com/article/10.1007/s00339-014-8271-0

KEYWORDS: Graphene, Anode, Pre-lithiation, Gravimetric 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: To provide architectures that enable propulsion systems upgrade/change with minimal cost and effort. To design modular, and self-adapting architectures to link new and legacy propulsion systems. 

DESCRIPTION: A propulsion system consists of a source of mechanical power, and a propulsor (means of converting this power into propulsive force). When it comes to integrated propulsion systems, there's lot of work that goes into power plant and propulsor matching on a performance level, before control ever gets involved. Hence the idea of core and prop/fan modules as separate elements that could be swapped around with a plug-and-play (PnP) system would be an efficient technology. Adaptive and peak-seeking control tools integrated in a decentralized architecture could enable PnP development of entire families of propulsion systems. The research includes the software and hardware aspects of the PnP technology development for propulsion systems. In the futuristic engine control vision, engine cores and props/fans could be purchased with their onboard subordinate controllers ready for integration into a functional propulsion system, whereas the FADEC was developed independently for the integrated engine. When it comes to integrated propulsion systems, there's lot of work that goes into power plant and propulsor matching on a performance level, before control ever gets involved. Hence the idea of core and prop/fan modules as separate elements that could be swapped around with a plug and play system would be an efficient technology. Helicopters and other VTOL aircraft systems might be good candidates though, since in those cases one could consider the core power plant as a swappable module. A given helicopter with a given set of rotor blades could be made to work with various Original Engine Manufacturers (OEMs) Furthermore, the PnP technology can be implemented in automobile and marine propulsion systems. The design approach would eliminate control interfaces compatibility issues. Commercial manufacturers of gas turbine engines rarely design all new engine centerlines; the lifespan of successful engine families is decades. Many of the new engines designed in a family are based on an existing engine core, primarily due to cost and reliability concerns. The high-pressure compressor and turbine contain the highest performance, and therefore most expensive, components. Engine core designs may move from military turbojets into commercial turbo-fans and turbo-props. A similar niche is occurring in UAV development, where small gas turbines are being used to power a variety of different lift/thrust devices. UAV development programs rarely have the resources for serious engine redevelopment and therefore must select from a limited number of commercial off the shelf (COTS) engines. In the case of small gas turbines these COTS engines are generally designed for missile turbojet or power generator applications, while the UAV designer may want to use the engine core in a turbo-prop or turbofan application. Successful development of decentralized adaptive control for this class of engines would allow UAV designers to purchase engines with onboard controllers and mate them with their own proprietary fan/prop sections without having to design a new control system from scratch. For propulsion system PnP technology development, adaptive and peak-seeking control techniques can be used. Adaptive control, for fuel regulation, and a self-tuning controller, for prop/fan angle regulation, integrated in a decentralized control architecture is the general structure of this PnP technology. Using this technology, the propulsion system fan/prop with its subordinate controller can be plugged in to the various propulsion system cores with their own subordinate controllers, which also include the supervisory controller, and vice versa. With the aid of this technique, different engine cores can be matched to different props/fans, and the whole propulsion system should work without any more performance tuning. For example, in geared turbofan engine systems, physical separation of core and propulsor provides an alternative to the geared fan architecture by enabling the integration of variable pitch fans in the geared turbofan engines using PnP technology. The plug and play technology can be applied for legacy as well as new engine design. Any changes in sensors, actuators, or software in this system should be considered as a part of the modular design. For example, using existing hardware with new hardware with minimum changes in the software. Appropriate embedded system design is also a part of the PnP technology development. This PnP technology has the potential to optimize the software/hardware integration for legacy and new generation turbine engines. New design approaches are needed in unmanned aerial vehicle (UAV) development, where small gas turbines are being used to power a variety of different lift/thrust devices. UAV development programs rarely have the resources for serious engine redevelopment and therefore must select from a limited number of commercial off the shelf (COTS) engines. In the case of small gas turbines, these COTS engines are generally designed for missile-turbojet or power generator applications, while the UAV designer may want to use the engine core in a turbo-prop or turbofan application. Successful development of PnP technology for this class of engines would allow UAV designers to purchase engines with onboard controllers and mate them with their own proprietary fan/prop sections without having to design a new control system from scratch. Some of the potential examples of propulsion systems for PnP technology application are presented here. In a UAV which has a few different propulsion systems in which they have had to integrate commercial power systems into the overall propulsor, either using one fan or several fans. Another application is a UAV which has an engine attached to a lift fan; the fan is fixed pitch and the motor is internal combustion, but a turbine application would require the incorporation of a variable pitch fan system. Another example could be the Pratt and Whitney (P&W) pure power geared turbofan engines which have been developed recently. The current versions of the engines utilize fixed pitch fans, but PnP technology can enable the integration of variable pitch fans in P&W geared turbofan engines. Gas turbine engine technology is a core element of many naval operations, including airborne assets and vessels relying on gas turbine propulsion technology. This plug and play technology could optimize the software/hardware integration for legacy and new generation turbine engines. Structuring engine control in a modular fashion using PnP technology would increase compatibility between different engine manufacturers and reduce development time and cost for new engines. PnP engine control technology also offers the potential of reduced engine weight, complexity, and maintenance needs, it also increases the flexibility in engine control systems. In addition, this architecture increases the reconfigurability/upgradability of propulsion systems where the data-bus, individual sensors and actuators, as well as computers, can be replaced and, possibly, updated, without forcing the disassembly/re-assembly of many engine components. 

PHASE I: Conceptual development of the PnP technology which includes the decentralized adaptive controller with a self-tuning control loop to be used for engine core and fan/prop subsystems and numerical simulation of this technology for a small turbofan engine. This stage is mostly focused on the software and simulation aspect of PnP technology development. 

PHASE II: The outcome of the first task would then be validated on a representative turbine engine, by investigating the necessary hardware and implementing the developed PnP technology. Based on the results of this experiment, update the controller architectures as necessary. Working with turbine engine manufacturers is encouraged. 

PHASE III: Integrate the outcomes of the Phase I and II tasks in a finalized software and hardware platform and develop it as a PnP technology for modular propulsion systems. This technology can be tailored for any propulsion system in manned or unmanned aircraft such as gas turbine, hybrid-electric engine, or piston engine specifically. 

REFERENCES: 

1. Distributed Engine Control Working Group DECWG), "Transition in Gas Turbine Engine Control Systems Architecture: Modular, Distributed, Embedded," NASA Propulsion Controls and Diagnostics Workshop, Dec. 8-10, 2009.; 2. United States Air Force Chief Scientist, "Technology Horizons: A Vision for Air Force Science and Technology," AF/ST-TR-10-01-PR, Volume 1, May 2010.; 3. M. Pakmehr, “Towards Verifiable Adaptive Control of Gas Turbine Engines,” Chapter V: Plug and Play Technology Concept for Gas Turbine Engine Control System, Ph.D. Thesis, Georgia Institute of Technology, May 2013.; 4. J. Bendtsen, K. Trangbaek and J. Stoustrup, "Plug-and-Play Control—Modifying Control Systems Online," in IEEE Transactions on Control Systems Technology, Vol. 21, No. 1, pp. 79-93, January 2013.

KEYWORDS: Plug-and-Play (PnP), Modular Design, Decentralized Control Architecture, Adaptive Control, Turbine Engine, Propulsion Systems, Online Control Tuning, Reconfigurable System 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop and demonstrate a high-performance, rechargeable, printed, solid state battery with a specific energy >250 Wh/kg at a C/5 rate. The battery must maintain >500 cycles over an operating temperature range of 0 degrees C to 50 degrees C with humidity conditions ranging from 0 to 100 percent while sustaining a high level of performance. 

DESCRIPTION: The emphasis of this topic shall be on the development of aerosol jet, inkjet printing, syringe deposition or non-vacuum deposition technologies to demonstrate printed all-solid state batteries with a specific energy >250Wh/kg at a C/5 discharge rate, and an objective 4 Ahr cell size. The cell should be capable of maintaining a constant discharge rate up to 2C, as well as, have the ability to operate under these conditions over a wide temperature (0 degrees C to 50 degrees C) and humidity (0 to 100 percent) range. The Battlefield Air Operations (BAO) Kit's capability description document (CDD) provides many key performance parameter (KPP) and key system attribute (KSA) requirements addressed in this project. The focus of this project is to provide battlefield airmen (BA) with a safe, energy dense power source for dismounted missions. The BA worn system is only one of many military assets relying on rechargeable batteries as their power source. There continues to be an increasing need for batteries with more electrical energy and power as the capabilities for these systems continue to improve. The increasing need for additional batteries to support these growing power and energy demands comes with added weight and mounting space limitations. The BA can carry in excess of 30 lbs. of batteries, including BB-2590s, to support a single mission. Solid state battery technology is one approach toward enabling the use of high energy-dense electrode materials, which will help limit the weight of the batteries the warfighter will need to carry, while providing a safer Li-ion battery solution. One of the limiting factors for solid state batteries is the high interfacial charge transfer resistance between the electrodes and electrolyte, as well as the conductivity of the electrolyte. This limits operation at lower temperatures and high discharge rates (up to 2 degrees C). Solid state batteries provide the opportunity of increased cycle life and shelf life with dendrite formation and growth suppression. In addition, solid state batteries may enable the utilization of high voltage / high energy electrode options since solid state electrolytes are known to exhibit good electrochemical stability and a wide electrochemical window, thus further improving the energy density. The focus of this effort is to explore the use of 3-D printing mask-less deposition techniques, such as aerosol jet, inkjet printing, syringe deposition, or non-vacuum deposition technologies as a potential approaches to provide intimate contact between electrode and electrolyte layers, which will address the interfacial charge transfer resistance. 3-D printing techniques provide the ability to functionally engineer the cell layers, as a mean to lower interfacial charge transfer resistance, thereby improving Li-ion transference, cycle life, as well as, overall battery performance. Furthermore, the ability to use a more automated 3-D printing processing technique could not only enable the solid state battery technology to be readily scaled to a range of cell sizes but also reduce manufacturing costs. This will allow for the realization of solid state batteries which can provide a safer, more robust product for the warfighter in comparison to the current conventional cells which contain a volatile liquid electrolyte. 

PHASE I: Design and define performance parameters/integration constraints for the battery. Demonstrate feasibility of a printed solid state battery. Demonstrate overall performance improvements when compared to a common lithium ion battery. Provide testing to prove safe and reliable charge/discharge capabilities, and performance in various temperature (0 degrees C to 50 degrees C) and humidity conditions (0 to 100 percent). 

PHASE II: Develop and demonstrate a prototype 4Ah solid state 3-D printed cell with the ability to meet the stated metrics above. Demonstrate and validate the ability to meet required performance. Demonstrate the safety improvements and the operational conditions, structural robustness, and energy/power efficiency to meet design metrics. Conduct a formal risk assessment of the printed solid state battery, projected cost analysis for manufacturing, and document key program risks. Deliver a prototype printed solid state battery to AFRL for testing and analysis. 

PHASE III: Mature technology and produce representative articles for operational test assessments. Submit production representative articles for certification. Provide operator and maintainer manuals. Develop and refine cost and schedule estimates for full rate production. 

REFERENCES: 

1. Kim, S., et al., "Printable Solid-State Lithium-Ion Batteries: A New Route toward Shape-Conformable Power Sources with Aesthetic Versatility for Flexible Electronics," ACS Nano Letters 15, 5168-5177 (2015).; 2. Gu, Y., et al., "Fabrication of rechargeable lithium ion batteries using water-based inkjet printed cathodes," Journal of Manufacturing Processes 20, 198-205 (2015).; 3. Lawes, S., et al., "Inkjet-printed silicon as high performance anodes for Li-ion batteries," 36, 313-321 (2017).; 4. Blake, A., et al., "3D Printable Ceramic-Polymer Electrolytes for Flexible High Performance Li-Ion Batteries with Enhanced Thermal Stability," Adv Energy Mater 1602920 (2017).

KEYWORDS: Solid Electrolyte, Aerosol Jet, Inkjet, Additive Manufacturing, Rechargeable Solid State Battery, Battlefield Airman, Safety 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop and apply erosion-resistant coatings to lift fan blades and/or large-diameter IBRs (integrally bladed rotors) for large Short Take-off and Vertical Landing (STOVL) aircraft.  

DESCRIPTION: Aircraft operating in sand/dust environments experience erosion of the gas turbine engine compressor airfoils that deteriorates engine performance; increases fuel consumption; increases maintenance, logistic support, and costs; and decreases safety-of-flight. This will present a particular challenge for large STOVL aircraft, which are likely to ingest large amounts of abrasive particles during the critical take-off and landing stages of operation. While the implementation of inlet barrier filters has provided some protection for helicopter engine compressor airfoils, that solution will not help here because the lift fan blades in a STOVL aircraft are directly exposed to the full force of any dust or debris that may be kicked up from the ground during lift-off and landing. The successful application of erosion-resistant coatings designed to handle those particular conditions will be key to sustaining safety of flight and aircraft system performance. Historically, the application of erosion-resistant coatings in the compressor section of helicopter engines operating in desert environments has resulted in increased engine time-on-wing and engine performance retention. However, the compressor airfoils in helicopter engines are much smaller (typically 10 cm or less in length) than the compressor airfoils on some large STOVL aircraft engines’ IBRs. For example, a first-stage IBR can measure approximately one-meter in diameter. These large-size IBRs are expensive to manufacture and replace. Hence, the potential of an erosion-resistant coating maintaining component efficiency and delaying component degradation of large-diameter IBRs will be critical in reducing total operating costs. A previous SBIR topic (N08-144) focused on developing an erosion-resistant coating with damping properties for the compressor airfoils on the JSF aircraft’s integrally bladed rotors (IBR), but that effort ended well short of implementation. This project seeks erosion-resistant coatings for the much more vulnerable lift fan blades and main engine IBRs on a production basis. The coatings must be able to withstand the austere operating environments of gas turbine engines such as high cycle fatigue (HCF) and stresses due to surge and aerodynamic and centrifugal loads. At the same time, they should not spall or delaminate after absorbing foreign object damage. 

PHASE I: Determine the feasibility of applying erosion-resistant coatings on large-diameter engine fan/compressor IBRs and lift fan blades. 

PHASE II: Demonstrate the application of the coating on a large-diameter IBR and/or lift fan blade. Conduct erosion tests on current bill-of-material and coated large-diameter IBRs and/or lift fan blades to characterize the baseline erosion rates. Develop a plan for productionizing the coating process for large-diameter IBRs and/or lift fan blades, including estimates for non-recurring and recurring costs to apply production coatings, and predict savings and benefits for large STOVL aircraft engines. 

PHASE III: Transition application of the selected erosion-resistant coatings to the JSF engine compressors and/or lift fan IBRs. The application of erosion-resistant coatings on large diameter compressor airfoils and IBRs has potential application for compressor airfoils on large turbofan engines powering commercial aircraft fleets. 

REFERENCES: 

1. Valleti, Krishna, Puneet, C., Rama Krishna, L., and Shrikant V Joshi, “Studies on cathodic arc PVD grown TiCrN based erosion resistant thin films,” Journal of Vacuum Science and Technology A: Vacuum, Surfaces and Films. Vol. 34 (4), Article number 041512. July 1, 2016. ; 2. Urbahs, A., Rudzitis, J., Savkovs, K., Urbaha, M., Boiko, I., Leitans, A., and Lungevics, J., "Titanium compound erosion-resistant nano-coatings", Key Engineering Materials, Vol 674 (2016) PP 283-8.; 3. SBIR topic N08-144 (Erosion Resistant Coatings for Large Size Gas Turbine Engine Compressor Airfoils); solitation number 2008.2

KEYWORDS: Erosion; Resistant; Coatings; Airfoils; Lift Fan Blades; Gas Turbine Engines 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop and demonstrate a novel high energy (>400Whr/kg) rechargeable lithium battery technology to provide high quality enduring power for Battlefield Airmen wearable electronics and small unmanned aerial system (SUAS) applications. 

DESCRIPTION: The focus of this project is on providing Air Force Special Operations Command (AFSOC) battlefield airmen (BA) with a high performance, energy-dense power source for extended runtime on dismounted missions. A significant number of military assets, including multiple types of soldier-worn systems, rely heavily on power provided by rechargeable batteries. As the capabilities of these systems increase to support current and future mission sets, there is an ever-increasing need for batteries with more electrical energy. Recent advancements in high energy electrode chemistries (e.g. Lithium metal anode, Silicon anode, nanostructured high energy cathode materials) have proven feasible for achieving specific energy densities (i.e. increased amount of stored energy for the equivalent weight) in excess of 400 Whr/kg, or approximately a 1.6X improvement over state-of-the-art Li battery technology. Specifically, lithium metal has always been considered as a “Holy Grail” of anode materials for high-energy-density batteries owing to its extremely high theoretical gravimetric capacity of 3860 mAh/g and the lowest electrochemical potential of 3.04 V. Unfortunately, significant safety challenges still exist, including dendrite growth and complex interfacial reactions, which have limited its transition to practical applications. The objective of this topic is to develop and demonstrate a novel rechargeable lithium battery with a specific energy >400 Whr/kg at C/5 discharge rate, able to maintain an objective cycle life of >250 cycles at 80 percent capacity and operate over a wide temperature range of -30 degrees C to + 49 degrees C and varying humidity conditions (0 to 100 percent). The high energy cell should have the ability to operate up to a 2C continuous discharge rate at the stated operational conditions, as well as be stored over a wide temperature range -40 degrees C to +70 degrees C. A strong focus will be on optimization and maturation of the technology for military use and safety. This topic will not consider the use of lithium sulfur or metal air batteries as proposed solutions. 

PHASE I: Design and define performance parameters/integration constraints for the battery. Demonstrate feasibility achieving the stated metric on the proposed high energy battery solution. Demonstrate overall performance improvements when compared to a common lithium ion battery. Provide testing to prove the ability to achieve safe and reliable charge/discharge capabilities, cycle life, and performance. 

PHASE II: Develop and demonstrate the high energy Li battery solution at a cell capacity of at least 4Ah, with the ability to meet the stated metrics above. Demonstrate and validate the ability to meet stated design metrics above. Develop test plan and conduct laboratory testing to confirm performance. Conduct a formal risk assessment of the high energy battery solution for transportation, storage, and use in an operational environment, perform a projected cost analysis for manufacturing, and document key program risks, as well as risk mitigation steps. Deliver a prototype high energy rechargeable Li battery cells to AFRL for testing and analysis. 

PHASE III: Mature technology and produce prototype battery packs for operational test assessments. Submit production representative articles and pass UN/DOT and MIL-STD-810G testing and certification. Develop and refine cost and schedule estimates for full rate production. 

REFERENCES: 

1. S.F. Liu, et al., "Recent development in lithium metal anodes of liquid-state rechargeable batteries," Journal of Alloys and Compounds, 730, 135-149, 2018.; 2. Zheng-Long Xu, et al., "Nanosilicon anodes for high performance rechargeable batteries," Progress in Materials Science, 90, 1-44, 2017.; 3. Md-Jamal Uddin, et al., "Nanostructured cathode materials synthesis for lithium-ion batteries," Materials Today Energy, 5, 138-157, 2017.; 4. Arumugam Manthiram, et al., "A perspective on nickel-rich layered oxide cathodes for lithium-ion batteries," Energy Storage Materials, 6, 125-139, 2017.

KEYWORDS: High Energy Lithium Battery, Rechargeable Lithium Battery, Secondary Lithium Battery, High Energy Battery Electrodes, Energy Storage, Portable Power 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Design and develop a form-fit-and-function replacement for Aluminum in Ammonium Perchlorate Compound Propellant (APCP) solid rocket propellant that produces minimum HCl and aluminum slag bi-products while maintaining equivalent or better combustion efficiencies (c*), and maintaining or improving munition safety rating. Minimize performance degradation due to water condensation on proposed fuel grain during storage, transportation, and flight operations. 

DESCRIPTION: High performance solid rocket propellants currently have two primary problems: the metal fuel (aluminum powder) sinters and agglomerates at the propellant surface, forming large molten droplets (LMD) which burn slowly and cause significant two-phase flow losses as the LMD pass through the nozzle; and they use ammonium perchlorate as an oxidizer, which also forms copious amounts of corrosive hydrochloric acid (HCl) during combustion. These bi-products are harmful to the atmosphere, and degrade the space environment by producing debris in the form of Al slag which can co-orbit and collide with resident space objects. Some replacement fuels have yielded propellants that have reduced performance (lower specific impulse), only work at low altitudes, and/or become unsafe to handle (detonable). For air-launched missile applications, a munition may be loitered at a colder, higher altitude for an extended period of time; and then be returned to a warmer, low altitude environment. Condensation is likely to occur, resulting in the fuel being compromised. 

PHASE I: Design a solid rocket fuel propellant to replace the current fuel used in munitions and rocket boosters which reduces degradation due to water condensation, maintains or improves munition insensibility, and produces thrust equivalent to or greater than that of current solid rocket fuel propellants. Major Milestone for Phase I is to assess the safety and material compatibility of proposed fuel material by itself and in relevant propellant formulations. This includes fully characterizing the material handling concerns and protocols. The overall objective of the Phase I work is to develop one to two candidate self-fragmenting structural reactive materials (SF-SRM) that can be used as a novel explosive ordnance casing material. This effort could include developing and manufacturing self-fragmenting, self-reacting materials (SF-SRM) for preliminary testing; testing the sensitivity of SF-SRM materials for electrostatic shock, friction, and drop-weight impact; investigating the microexplosive tendency of the candidate SF-SRM materials under high heating rates; and investigating the casing combustion efficiency of pellet size candidate SF-SRM powders under strong explosive shock. 

PHASE II: Build and test, in a relevant environment, the above described solid rocket fuel propellant. Phase II milestones include determining burn rate and pressure exponent for a relevant formulation as well as determining small-scale ballistic performance and mechanical properties. Further, accelerated aging studies and cold-soak tests will be conducted to give an indication of shelf life. 

PHASE III: Milestones will include formulation optimization, performance assessment under high-fidelity laboratory conditions, and engineering trade studies to assess the utility/benefit of the material based upon delivered density*Isp. Military Application: Use as a fuel replacement in a prototype solid rocket fuel rocket motor in a sounding rocket or small-scale missile. For air-launch, use in precision guided munitions propellant to ensure quick and reliable response to adversarial activities. Civilian Application: Use as a rocket fuel propellant replacement for civilian solid fuel rocket launches. Here, the reduction in HCl acid and Al slag is useful in minimizing the negative environmental impact, allowing more frequent launches. 

REFERENCES: 

1. B.C. Terry, I.E. Gunduz, M.A. Pfeil, T.R. Sippel, and S.F. Son. "A mechanism for shattering microexplosions and dispersive boiling phenomena in aluminum–lithium alloy based solid propellant". https://www.sciencedirect.com/science/article/pii/S1540748916301572; 2. Terry, B., Sippel, T., Pfeil, M., Gunduz, I., and Son, S., "Removing Hydrochloric Acid Exhaust Products from High Performance Solid Rocket Propellant Using Aluminum-Lithium Alloy", Journal of Hazardous Materials (2016).

KEYWORDS: APCP, Solid Rocket Fuel Propellant, Rocket Booster, Munitions, 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: To develop innovative propulsion concepts that address the increasing agility requirements of Air Force and DoD spacecraft. 

DESCRIPTION: Future DoD spacecraft will need greater agility to change orbits for mission requirements or to avoid the increasing hazards in crowded orbits. An agile spacecraft is one that can make an orbital change while maximizing propulsive life through propellant conservation. Agility requires, at minimum, propulsion concepts that are able to trade specific impulse (Isp) with thrust over a wide range as mission needs require. Short notice needs would require high thrust at the expense of propellant. Mission needs that have less severe time constraints can use high Isp and conserve propellant. However, a truly agile spacecraft will require both high thrust and high Isp simultaneously, at least for short periods of time. This topic seeks to develop in-space propulsion concepts that can be operated for short periods of time at high Isp and high thrust simultaneously. By high thrust, it is meant that the thrust is higher than a typical Hall thruster but can be less than a typical spacecraft chemical thruster, on the order of a few tens of newtons. By high Isp it is meant that the Isp is much higher than a chemical thruster, on the order of 1000 seconds or higher. By short period of time it is meant that large orbital maneuvers can be made impulsively instead of by spiral changes. It is anticipated that successful SBIR efforts will take advantage of increasingly efficient, low mass batteries or ultra-capacitors while carefully managing system mass so that the spacecraft mass fraction does not become unreasonable. This topic is looking for responsive propulsion giving high delta-V more characteristic of chemical propulsion while using a small fraction of propellant that a chemical thruster would use. Offerors are encouraged to also suggest innovative orbital maneuver strategies that might be enabled from their proposed solution. Current spacecraft propelled by electric thrusters use Hall thrusters that are too low in power to provide true agility. Additionally, current spacecraft do not have the power capability to supply a larger electric thruster. However, current energy storage devices could enable the use of high power electric thrusters using existing spacecraft photovoltaic systems. High thrust enables faster large orbit changes to mission altitudes. Once on orbit, a larger thruster could provide rapid acceleration and large delta-V with the use of energy storage. Current Hall thruster technologies may be a good fit at higher Isp, where many designs are approaching 70% efficiency, close to the limitations of physics. It is not as clear that Hall thrusters are a good solution at an Isp of 1000s or lower as their efficiencies drop off rapidly. Therefore, this topic will allow electric propulsion technologies other than Hall thrusters. Lower Isp allows higher thrust to power which would reduce orbit transfer times, yet be much more efficient in propellant than chemical thrusters. Proposed solutions should also be compatible with typical DoD spacecraft. The possibility of spacecraft system contamination should be addressed. The proposed propulsion concept should not limit spacecraft lifetime, most of which have expected lifetimes of 15 years. No unusual thermal, power, or balance constraints should be placed on the spacecraft by the proposed concept. 

PHASE I: Select propulsion concepts and identify how spacecraft agility could be improved by these concepts. A proof of concept demonstration is desirable. Technical challenges or barriers should be identified. An approach to a phase II effort should be outlined. 

PHASE II: Further develop the Phase I effort by building and testing a prototype thruster or thruster system including a propellant feed system. Government Furnished test facilities and hardware may be available so the proposer should request if desired. Further interaction with Spacecraft Prime Contractors would be desirable. 

PHASE III: Transition the technologies developed under this topic to a demonstration flight and space qualification. 

REFERENCES: 

1. Gulczinski, F. S., et al., “Micropropulsion Research at AFRL,” AIAA-2000-3255, 36th Joint Propulsion Conference, Huntsville, Alabama, 2000.; 2. Hawkins, T.W., Brand, A.J., McKay, M.B., and Ismail, I.M.K., “Characterization of Reduced Toxicity, High Performance Monopropellants at the U.S. Air Force Research Laboratory”, Fourth International Conference on Green Propellants for Space Propulsion, Noordwijk, NL, June 2001.; 3. Koelfgen, Syri, et. Al. “A Plasmoid Thruster for Space Propulsion”, AIAA-2003-4992. Joint Propulsion Conference, 2003.; 4. E.Y. Choueiri and J.K. Ziemer. “Quasi-Steady Magnetoplasmadynamic Thruster Performance Database”. Journal of Propulsion and Power, 17:967–976, 2001. September-October.

KEYWORDS: Electric Propulsion, MagnetoPlasmaDynamics (MPD), Spacecraft Propulsion, Advanced Propulsion, Magneto Hydrodynamics (MHD), Plasma 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Design and development of a cost-effective test bed capability or experimental setup for gas turbine engine control and sensor systems. 

DESCRIPTION: Modern gas turbine engine designs are being influenced by increased levels of instrumentation and control that enhance the overall performance. Variable cycle engines have increased the level of authority that control system developers have over the engine cycle. The number of control variables and sensors have increased by over 50 percent. These advanced engine cycles require instrumentation feedback which then allows the digital engine controller to optimize the engine performance. The reliance on data dependency along with the continued decrease in price of electronics and instrumentation over the course of the last several decades has fueled this move toward more heavily instrumented engines. This, in turn, has led to significant improvements in instrumentation and control authority, resulting in innovative measurement modalities and control schemes. There is, however, a paucity of experimental testing infrastructure to adequately and reliably test control paradigms and distributed instrumentation in an actual gas turbine environment under nominal operating conditions. This is especially necessary since past development of sensors and control concepts is typically carried out with sub-scale experimentation which limits the testing of true actuator behavior. This lack of capacity to test equipment on an operating gas turbine presents an obstacle in the path towards developing new sensor and control technology that side-step issues of scalability, closed loop control and bottlenecks of bandwidth, frequency response and authority. The USAF is seeking a new test bed / experimental setup to be designed and developed which will provide cost-effective testing for newly developed sensors, actuators or control schemes in support of USAF objectives. The new test bed should have multiple options for including traditional and novel sensor technologies in a variety of gas turbine type environments. This includes compressor inlet and discharge, turbine inlet and discharge, and even the combustion zone. The new system should also have a flexible control system that can be updated to include third-party control schemes to interact with the existing sensor and actuator network. 

PHASE I: Design an experimental setup/test bed with the basic sensors and actuators typically found in gas turbine engines, and access for additional and nontraditional sensors and actuators for future application and testing of advanced control strategies. Design a control system to interact with the sensors and actuators to achieve basic engine control (start, steady state operation, transient throttle events, and shutdown), as well as, flexibility to experiment with other novel control strategies. 

PHASE II: Fabrication and commissioning of the test bed/experimental setup to include demonstration of the full range of operating conditions as designed, including demonstration of the control modes of the test system. 

PHASE III: Conduct performance testing of sensors, actuators and control schemes relevant to USAF turbine engines or other aerospace vehicle applications. 

REFERENCES: 

1. Behbahani, A. and Tulpule, B., “Perspective for Distributed Intelligent Engine Controls of the Future”, AIAA 2010-6631, 46th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Nashville, TN, 25- 28 July 2010.; 2. Millar, R. and Tulpule, B., “Intelligent Sensor Node as an Approach to Integrated Instrumentation & Sensor Systems for Aerospace Systems Control”, AIAA 2011-1598, Aerospace 2011, St. Louis, MO, 29- 31 March 2011.; 3. Tooley, J.J. et.al., “Design and System Implementation Considerations for High Temperature Distributed Engine Control”, AIAA 2010-6674, 46th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Nashville, TN, 25-28 July 2010.; 4. Pakmehr, M., Fitzgerald, N., Cazenave, T., Feron E., Paduano, J. D., and Behbahani, A., "Distributed Modular Control Architecture Development for Gas Turbine Engines", Proceedings of the ISA 58th International Instrumentation Symposium, San Diego, CA

KEYWORDS: Gas Turbine, Engine Controls, Variable Cycle, Sensors, Actuators, Experimental Setup 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop an advanced riblet system (ARS) to reduce viscous drag on medium altitude long endurance aircraft (MALE) to increase range/time-on-station (TOS). Riblet application should be fast (m^2/min), compatible with depot processes/timelines, and produce structures resistant to fouling. 

DESCRIPTION: A significant source of aircraft drag is skin friction drag; the drag caused by the friction of air against the surface of an aircraft in flight. For a typical MALE aircraft the skin friction drag is about 1/3 of the total aircraft drag. Reducing skin friction is an obvious target for increasing aircraft performance (range or TOS). MALE aircraft usually achieve their performance in part by having laminar flow boundary layers (BL) on some surfaces (e.g. wings); the skin friction of a laminar BL is an order of magnitude less than that of a turbulent BL. They are designed to have the maximum extent of laminar flow practical and achieving more would be extremely difficult. However there are technologies for reducing the skin friction of the remaining turbulent aircraft BLs. Riblets are one such technology. 2D riblets are sized (peak-to-peak and peak-to-valley) to exclude the turbulent BL flow structures (which have a characteristic spanwise dimension) from “scrubbing” a significant portion of the surface; resulting in the flight-proven 6 percent skin friction drag reduction. Since skin friction drag is about 1/3 of the total drag of a MALE aircraft a 6 percent skin friction drag is equivalent to 2 percent drag reduction at the system (aircraft) level. (Note that this is a theoretical maximum since it is not possible to apply riblets to 100 percent of the OML with a turbulent BL.) 2D riblets have been flight tested on an A320 transport aircraft with about 2/3 of the aircraft’s surface covered with riblets. The A320 is typical of most Mil and Civ transport aircraft flying today; skin friction is approximately 50 percent of the total aircraft drag. With the 6 percent reduction in skin friction drag due to the riblets the total aircraft drag reduction achieved was 2 percent (2/3 x 50 percent x 6 percent). Despite the flight-proven 2percent transport aircraft drag reduction 2D riblets they have not transitioned to Mil or Civ aircraft because 1) excessive application time (current state-of-the-art (SOTA) is an adhesive-backed applique), and 2) limited duration (1-2 years) of the drag reduction effect due to the microscopic riblet grooves becoming fouled (dirt, hydraulic fluid, etc). Both of these factors have a negative impact on ROI, preventing transition. The SBIR will address these transition hurdles. A direct contactless microfabrication method (DCM) will “print” the riblets into a photo-curable aircraft topcoat. Advanced (3D) riblets will be designed, yielding 2.5-times the skin friction drag reduction as current 2D riblets. Superhydrophobic coatings will be incorporated into the ARS to keep it clean and functional for an entire programmed depot maintenance (PDM) cycle. An ultra-precision drag balance will be developed to aid development and performance validation of the ARS. As such this SBIR will close the gap between the theoretical promise of riblet technology for skin friction drag reduction, and its practical application to the U.S. Air Force fleet. It is recognized the multifaceted aspect of this topic will make it challenging for a single small business. 

PHASE I: Investigate DCM scale-up (ref 2) by examining use of multiple LEDs and assessing robotic- or gantry-based systems for optical head movement. Assess design variables for 3D riblets (ref 3) numerically (CFD) and develop experimental validation plan. Examine coating chemistries and refine aircraft-compatible application processes to improve the durability of superhydrophobic coatings (ref 4). Design an ultra-precision balance with milli-Newton resolution. 

PHASE II: Design and fabricate a scaled-up prototype DCM system capable of applying 3D riblets to a major portion of an aircraft (wing or fuselage section) at speeds on the order of m^2/min; mature 3D riblet designs with continued CFD simulations; use the DCM method to produce and wind tunnel test the ARS, using the ultra-precision drag balance designed in Phase I; create the superhydrophobic coatings with the chemistries and application techniques identified in Phase I. Validate the durability of the coatings using ASTM tests and determine thickness to adjust riblet dimensions to compensate. 

PHASE III: Develop and commercialize a full scale DCM system capable of applying an ARS to military and commercial aircraft. The ARS will be comprised of optimized 3D riblets and Superhydrophobic coatings with effects lasting an entire PDM cycle (nominally 5 years). Commercialize the ultra-precision skin friction balance. 

REFERENCES: 

1. Viscous Drag Reduction on Transport Aircraft, AIAA 91-0865.; 2. Microfabrication of Riblets for Drag Reduction, AIAA-2018-0321.; 3. Design and Testing of 3-D Riblets, AIAA-2018-0324.; 4. Designing Superhydrophobic Coatings for Aircraft Drag Avoidance, AIAA-2017-0282.

KEYWORDS: Aircraft, Drag, Reduction, Passive, Viscous, Skin Friction, Riblet, Superhydrophobic, Force, Measurement 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a safe and low maintenance Li ion battery replacement for the MQ-9 unmanned aerial system (UAS), able to support a 365-day inspection interval in order to reduce aircraft downtime without degrading the current system specifications. 

DESCRIPTION: The objective of this topic is to design and develop a lithium ion battery- based solution as a potential NiCd battery replacement as a means to minimize the sustainment requirements with a 365-day inspection interval objective, as well as increasing the power and energy available onboard the aircraft. Unmanned aerial systems (UASs) have become an essential asset for U.S. military forces, and increasingly by allied forces, to help establish battlefield superiority in today’s hot zones, allowing for more precise weapons targeting and better protection over friendly forces. The use of these weapon systems have and continue to provide unparalleled real-time information to the ground forces to support both the Global War on Terrorism and humanitarian relief missions. Therefore, any substantial aircraft downtime due to routine or unwarranted maintenance need to be minimized for optional…… Battery reliability and maintainability with the existing NiCd battery has become a substantial issue that can drive sustainment costs and aircraft downtime. Improving the overall efficiency and effectiveness of the battery with a new technology solution will not only reduce sustainment costs but can also help to improve the SWaP (size, weight, and power) as well as capacity. The primary focus of this effort shall be on developing a safe, sustainable battery solution, not only during operation, but also address the logistics challenges of any specialized transportation, storage, and handling requirements. UN/DOT 38.3 and Navy Instruction 9310 shall be used to determine reasonable lithium ion battery safety considerations. The solution should be as close to a form/fit/function replacement as possible. The existing NiCd battery specifications are as follows: nominal 25.2V (16.8V cut-off), 16Ah capacity, specific energy density 44.3 Wh/kg (cells only), volumetric energy density 836.1 Wh/L (cells only), max continuous discharge rate of 5C at the battery level, and nominal charge rate of C/3. The operating environment is -40 degrees C to +60 degrees C and 0 percent to 100 percent humidity, with a non- operating environment requirement of -40 degrees C to +70 degrees C. Aircraft design changes to enable battery compatibility should be kept to a minimum. Any changes required for integration of the battery solution shall be identified and documented. 

PHASE I: Determine feasibility of replacing the MQ-9 battery with a lithium ion battery based solution design with a 365-day maintenance inspection internal, while improving upon the baseline battery metrics stated above. Demonstrate through testing a safe solution can be achieved during all operational and non-operational conditions. Evaluate logistics impacts on the current MQ-9 transportation and storage infrastructure. Develop a plan to ensure battery replacement meets all required specs, identifying technical challenges and how these can be overcome. 

PHASE II: Develop and demonstrate Li ion-based MQ-9 battery, with the ability to meet the stated metrics above. Develop test plan and conduct laboratory testing to confirm safety and performance. Safety testing shall be performed in accordance with UN/DOT 38.3 and Navy Instruction 9310. Conduct a formal risk assessment of the battery solution for transportation, storage, handling and use in an operational environment, perform a projected cost analysis for manufacturing at full-rate, and document key program risks, as well as risk mitigation steps. Identify any impact replacement battery would have on current aircraft design, including software/hardware. Deliver a prototype Li ion battery to AFRL for testing and analysis. 

PHASE III: Fully mature technology replacement battery technology utilizing the structured MQ-9 upgrade strategy, to include providing drawings, delta specs, LG analysis, HW/SW Mx IETMs, etc. Submit production representative articles and pass UN/DOT 38.3 and MIL-STD-810G testing and certification. Once criteria is met, the solution may become a candidate for integration onto the platform. Develop and refine cost and schedule estimates for full rate production. 

REFERENCES: 

1. NAVSEA TM-S9310-AQ-SAF-010, TECHNICAL MANUAL FOR BATTERIES, NAVY LITHIUM SAFETY PROGRAM RESPONSIBILITIES AND PROCEDURES DISTRIBUTION. http://www.public.navy.mil/navsafecen/Documents/afloat/Surface/CS/Lithium_Batteries_Info/LithBattSafe.pdf (August 2004).; 2. MIL-STD-810G, DEPARTMENT OF DEFENSE TEST METHOD STANDARD: ENVIRONMENTAL ENGINEERING CONSIDERATIONS AND LABORATORY TESTS (15-APR-2014). http://everyspec.com/MIL-STD/MIL-STD-0800-0899/MIL-STD-810G_CHG-1_50560/.; 3. USAF MQ-9 Reaper Fact Sheet. http://www.af.mil/About-Us/Fact-Sheets/Display/Article/104470/mq-9-reaper/ (September 2015).; 4. M. Jacoby, "Assessing The Safety Of Lithium-Ion Batteries," Chemical and Engineering News, Vol 91, Issue 6, 33-37, (2013).

KEYWORDS: Aircraft Lithium Battery, Rechargeable Lithium Battery, Secondary Lithium Battery, Unmanned Aerial Vehicle, Energy Storage, Battery Safety 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop thermionic generation device technology that will take advantage of the extreme temperature within a hypersonic platform resulting in efficient thermionic conversion into electrical power while existing in a modular package to survive the harsh environment. 

DESCRIPTION: Thermoelectric generators (TEG) and Thermo-photovoltaics (TPV) are common candidates for energy harvesting studies, but the extreme internal temperature profile within a conceptual scramjet driven hypersonic vehicle presents a challenging design issue for TEG or TPV integration. Conceptual hypersonic aircraft are generally designed to be propelled by a non-rotating engine, such as a scramjet, prohibiting the use of conventional generators to draw electrical power from the engine. This fact, coupled with the extreme temperatures associated with hypersonic flight, has prompted studies of thermal-to-electric conversion of the excess heat energy on a hypersonic vehicle to provide electrical power to onboard systems. An alternative conversion technology that is especially attractive at higher temperatures is thermionic energy conversion. Thermionic devices have proven to provide high efficiency conversion from an extreme temperature source above 1800K and a reservoir “low” temperature in excess of 1000K. A thermionic energy conversion device consists of two metal electrodes separated by a narrow gap, where the high temperature emitter thermionically emits electrons into the gap and the collector absorbs them. This proposed program should address the application of modular thermionic conversion devices to convert internal heat within a hypersonic vehicle to electricity. The program should consider recent developments in micro-manufacturing and materials to reduce the interelectrode gap distance within the converter device and potentially eliminate the need for cesium vapor while suppressing the space charge effect. Device design should account for the harsh environment that includes high temperature and exposure to an oxidizing atmosphere and/or liquid fuel. Device operating temperatures should be explored between 1800K-2200K (emitter) and 800K-1200K (collector) with the potential for the temperature profile changing with time. The lifetime requirements could vary from a single use to a reusable system with 1 hour of power generation per use. The thermionic device power output goal would be 1-10 W/cm^2, which could be modularized to produce 10-100 kW of electrical power over 1 m^2 of surface area within the hypersonic vehicle. The work functions of the emitter and collector surfaces must be relatively low to develop a functional potential difference across the gap and draw electrical current through a load. The electron current through the gap can create a negative space charge which self-limits the current, so the negative space charge must be suppressed through device engineering. Significant engineering efforts were conducted in the 1960’s in the USA and Soviet Union to integrate thermionic conversion devices to space nuclear reactor or solar concentrator platforms for long duration operation. Typically, these devices included cesium vapor within a gap of ~0.1 mm to suppress the space charge and reduce the surface work functions. Thermionic conversion technology was demonstrated as feasible, but further development was curtailed for programmatic reasons. 

PHASE I: Design a thermionic conversion module that could operate for 1 hour within the high temperature and oxidizing environment of a hypersonic vehicle with a power output density >1W/cm^2. 

PHASE II: Fabricate and test thermionic conversion modules in simulated hypersonic vehicle operating conditions measuring power output and lifetime characteristics with the goal of 1 hour of operation at >1W/cm^2 . Deliver prototype module to AFRL/RQQE. 

PHASE III: Dual use commercialization: Explore military use applications of power generation for reusable hypersonic vehicles. Potential commercial applications could include direct conversion of fuel heat for remote electrical power with higher energy density than batteries. 

REFERENCES: 

1. Rasor, N.S., "Thermionic Energy Converter". In Chang, Sheldon S. L. "Fundamentals Handbook of Electrical and Computer Engineering." II. New York: Wiley. p. 668. ISBN 0-471-86213-4. (1983).; 2. Mahefkey, T., “Thermionics Quo Vadis?”, Washington, DC, USA: National Academy Press (2001).

KEYWORDS: Thermionic, Hypersonic, Direct Energy Conversion, Work Function 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop model order reduction strategies for electrical power and thermal components that retain high accuracy with reduced computational time for real time control and health monitoring applications. 

DESCRIPTION: Design and Verification of advanced propulsion and electric power controls requires reduced order models (ROMs) that run in real time. Calculation of power utilization, load factors, parameter estimates, and control mechanisms is a challenge as accurate, predictive algorithms may take an order of magnitude more time to execute (versus clock time) to reach a stable solution. It is desirable to reduce this computational burden to allow real time use of novel algorithms in control systems Propulsion Health Monitoring (PHM), and power and thermal architectures. It has been demonstrated that computational statistics (CS), machine learning (ML), and related artificial intelligence (AI) techniques that access large data sets can learn constrained domains without explicit programming. They can capture a large percentage of the requirements for accuracy of complex component and system loop (feedback) models of waste heat and transient power flow for electric actuation and high electric power usage components such as diode/fiber lasers. Use of key AI techniques such as CS and ML have the potential to reduce model/algorithm execution time by one or more orders of magnitude compared to the state-of-the-art. In the Phase I program, it is desirable to employ an Artificial Intelligence (AI) machine learning techniques to develop an integrated ROM for use in simulations of power and heat flow networks (feedback loops), electric actuation controls, and high power electric loads. The ROM should incorporate suitable component specific transient (high order) power and thermal sink characteristics expected in operational scenarios. The research should explore acceptable processing execution speed versus accuracy over the domain of interest. The ROM should consider future compatibility with relevant system demonstration hardware, such as execution on an engine control verifier bench, which interfaces a FADEC, and other real-time hardware in a closed loop. 

PHASE I: Select an AI machine learning methodology for prototype development of a Reduced Order Model (ROM) for control of high power electrical component energy flows (such as actuation, lasers) and waste heat. Ensure that the transient quality (high order effects) of the waste heat and electric power is considered. Evaluate suitable software and hardware architectures that reduce computational burdens, delays and communication uncertainties. Compare the performance of the ROM with a baseline representation of the system or component to determine the performance benefits and suitability for real-time applications. Participate in a workshop with the stakeholder (including all potential users of the tool) to insure that all requirements for the future prototype are clearly understood. 

PHASE II: Relevant modeling software will be coded, refined, and tested based on the Phase I design. Demonstration of the real-time high fidelity modeling capability will be performed on a state-of-the-art closed loop control system bench. Limitations and potential operational issues will be documented, as well as, applicability to targeted advanced propulsion, power and thermal systems. Develop a training manual and a transition plan to facilitate use of the tool in the design process by an engine or airframe company. 

PHASE III: Implementation and integration of the high fidelity capability will be accomplished. Real time and other performance issues with the Phase II design will be addressed and a fielded capability will be developed that meets the engine/aircraft power and thermal control system or thermal component operational requirements. Provide training to those identified in previous phases to accelerate transition to the field. 

REFERENCES: 

1. Konrad Rawlik, Marc Toussainty, “On Stochastic Optimal Control and Reinforcement Learning by Approximate Inference,” School of Informatics, University of Edinburgh, UK, Department of Computer Science, FU Berlin, Germany (2013).; 2. Neal Dawson-Elli, Seong Beom Lee, “Data Science Approaches for Electrochemical Engineers: An Introduction through Surrogate Model Development for Lithium-Ion Batteries,” Journal of the Electrochemical Society (2018).; 3. Jiequn Han, “Deep Learning Approximation for Stochastic Control Problems,” 1The Program of Applied Mathematics, Princeton University (2016).

KEYWORDS: Control Optimization, Machine Learning, Data Science And Optimization, Power And Thermal Optimal Control, AI Methodologies In Optimal Control, Supervisory Control Techniques 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Future aircraft-based high energy systems will produce hundreds of kilowatts of low-quality waste heat. So it is critical to integrate high energy system with propulsion, power, thermal, and controls for next generation aircraft. Novel approaches are sought to remove waste heat under these conditions without significant impacting the aircraft signature/aerodynamic performance. 

DESCRIPTION: The large quantities of low-quality (<40 degrees C/104 degrees F) waste heat generated by directed energy and other electrically based technologies need to be removed from air platforms in a manner that will allow the system to meet size, weight and power constraints and not interfere with aircraft operation. Heat from directed energy systems is often generated in laser diodes with junction temperatures from 20 degrees C - 30 degrees C (68 degrees F – 86 degrees F) as required for the desired pump laser wavelength. Most laser diode packages require non-electrically conductive working fluid with the current state of the art being de-ionized water which is undesirable for airborne logistics reasons. Due to the high peak heat flux of energy systems, thermal storage is often used during system firing and a smaller, steady heat sink will recharge the thermal storage. The heat removal capacity of fuel as working fluid is at or near its capacity in future and current air platforms. Heat sinks are being sought that do not involve transferring heat to the fuel. Non-fuel heat sinks have the potential to add to the aircraft thermal signature, radar cross section or adversely impact the aerodynamic performance of the platform. The successful proposal will investigate heat sinks which do not significantly impact the thermal signature, radar cross section or the aerodynamic performance of sub and transonic aircraft and which have the capacity to continuously remove up to 100kW of heat at less than <40 degrees C/104 degrees F at altitudes from 10kft to 40kft. It has a good potential on improving the performance of commercial aircraft. 

PHASE I: It will conduct a feasibility study on examining heat sinks involving a variety of technologies (propulsion, electric power, and thermal), evaluating them for performance, heat removal potential, SWaP, efficiency and effect on the aircraft flight worthiness. At a minimum, the following should be considered: retractable fins, louvered scoops, third stream engine air, convection from aircraft skin and blow-down of engine and exhaust compatible substances. The SBIR Company will be working with an industry partner (i.e. engine manufacturer or aircraft manufacturers). 

PHASE II: Based on Phase I feasibility study on heat rejection/sink results will build a subscale prototype system capable of being tested on surrogate heat sources in an appropriate vibration or wind tunnel facility. The Air Force Research Laboratory at Wright-Patterson AFB OH may be able to provide testing facilities for prototype system. The contractor may require base support during performance. Only U.S. Citizens will be permitted to work within AFRL Facilities. 

PHASE III: Demonstrate the prototype system on a compatible aircraft with a suitable directed energy system or surrogate heat source. Complements work on an initial demonstration of a high-powered laser pod to be flown on advanced aircraft in 2021 time frame. 

REFERENCES: 

1. Hitzigrath, R., "Improving Aircraft Fuel-Thermal Management," SAE Technical Paper 932086, 1993, doi: 10.4271/932086.; 2. Gray, Charles N., and Shayeson, Maurice W., "Aircraft Fuel Heat Sink Utilization," http://www.dtic.mil/cgi-bin/GetTRDoc?Location=U2&doc=GetTRDoc.pdf&AD=AD0912902.; 3. Karimi, Kamiar J., PhD, Senior Technical Fellow, "Future Aircraft Power Systems- Integration Challenges," Carnegie Mellon University Press, 2007.; 4. Swain, E.F., "Aircraft Avionics Cooling, Present and Future," Proceedings of the IEEE 1998 National Aerospace and Electronics Conference, NAECON 1998.

KEYWORDS: Propulsion, Power, Thermal Management, Directed Energy, Aircraft Heat Sinks, Low-Compatible, Integration, And Waste Heat 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop direct optically controlled, 1,200 to 2,000 V, 10 to 120 A, wide bandgap power switching device for applications in electro-hydrostatic (EHA) and electro-mechanical (EMA) actuator motor drives for air platforms. 

DESCRIPTION: Due to the inherent immunity of photonic technology to dynamic electromagnetic events, its application to power electronics used to drive flight-critical EHA and EMA surface control actuators is predicted to increase the reliability and survivability of these subsystems dramatically. Wide bandgap (WBG) power device technology has been under development for several years, targeting applications in DoD power communication systems requiring high-reliability and harsh-environment operability. Wide bandgap materials quantified power device performance benefits, in addition to its high temperature capability, include; improved component efficiency through reduced on-state and switching losses, lower on-resistance for high voltage devices, and higher frequency switching capability. As such, wide bandgap semiconductors are an emerging high reliability power device technology slated for utilization in several DoD platforms. Conventionally, passive and active filtering is used to reduce drive control susceptibility to large voltage and current switching transients and for suppression of parasitic oscillations inherent to electronic motor drive systems. However, these filters are incapable of protecting either the signal-level control electronics or the power devices themselves from catastrophic failure when exposed from external events and account for a significant volume and weight of the EHA/EMA electronics system. Optically-gated power semiconductors can minimize or eliminate the noise susceptibility of conventional power drive electronics. A successfully developed and fielded optically controlled EHA or EMA flight surface control subsystem could dramatically increase the survivability of air and other DoD platforms. An additional benefit is the possibility of reducing the volume and weight associated with conventional filters used to protect low-voltage control devices from the inherent radiated EMI associated with switching large voltages and currents. Lightweight, rugged, and compact optical sources that satisfy the requirements of repetition rate, optical power, and wavelength are required for direct device triggering. High device gain translates directly to reduced optical triggering power requirements thereby reducing the cost and operational complexity of the optical source. Therefore, considerations pertaining to the optical source and driving mechanism significantly impact the suitability of an optical power switch to satisfy the power system architecture specifications in a given platform. In order to make overall system efficiency comparable to state-of-the-art electrically controlled WBG power electronics, it is desired that a 1200 V switch requires less than 2 W of optical power per amp of continuous current. Research is also likely needed to develop an appropriate opto-electrical packaging scheme that reduces the triggering power loss and that can handle harsh environmental conditions. In summary, this topic is intended to investigate the area of optical control of wide bandgap power devices as it relates to power utilization and control technology that will satisfy stringent environmental requirements. The objective is to identify and address specific technology limitations and pursue solutions based on sound physical principles, which can lead to the development of robust, optically controlled power technology that can be utilized in EHA/EMA motor drives and other electrical power applications on DoD platforms. 

PHASE I: Demonstrate the feasibility of new and innovative wide bandgap direct optical switching power devices. The development of a fundamental switch structure design, with the fabrication and characterization of a scaled prototype, is highly desirable. The device should block at least 1000 V and conduct greater than 10 A of current. The temperature capability of the device should support operating at 150 degrees C. 

PHASE II: Develop and optimize full-scale, prototype, optically triggered wide band gap switches. Perform detailed static and dynamic electrical and optical characterizations of switch performance. Develop package design for optical integration and high power handling. Successfully integrate the prototypes into a representative power electronic component (converter, inverter, motor drive, etc.) for an equipment-level demonstration of the desired functionality using only optical control signals. 

PHASE III: Military application: This technology could lead to insertion in a variety of military applications. Potential aviation applications include directed energy weapons, motor drives, power converter, power inverters, and other representative power electronic components. 

REFERENCES: 

1. T. L. Weaver and R. H. Smith, “Photonic Vehicle Management,” 20th Digital Avionics System Conference, Daytona Beach, FL, October 2001.; 2. D. J. Halski, “Fly-by-light Flight Control Systems,” McDonnell Douglas Aerospace, Proc. SPIE, Fly-by-Light: Technology Transfer, Vol. 2467, p. 34-45, 1995.; 3. S. K. Mazumder and T. Sarkar, “Optically-triggered Power Transistor (OTPT) for Fly-by-light (FBL)/EMI Susceptible Power Electronics,” IEEE Power Electronics Specialists Conference, pp. 1-8, 2006.; 4. J. S. Sullivan, “Wide Bandgap Extrinsic Photoconductive Switches, “Lawrence Livermore National Laboratory Report LL LLNL-TH-523591, January 20, 2012.

KEYWORDS: Fly-by-light, Power-by-wire, Photonics, Power Electronics, Wide Bandgap Device, Optical Isolation, Gallium Nitride Semiconductors, Electrical Actuators, High Electric Field Protection, EMI 

TECHNOLOGY AREA(S): Space Platforms 

OBJECTIVE: Develop and demonstrate an additively manufactured reactor for a 1N AF-M315E thruster. 

DESCRIPTION: The last decade witnessed a tremendous rise in additive manufacturing capabilities. Today, numerous companies specializing in additive manufacturing are now capable producing complex parts from a variety of materials, including platinum group metals. This relatively new capability is of particular interest to the spacecraft propulsion community. Additive manufacturing of platinum group metals enables the creation of custom, complex, and often times small parts which may have been too expensive, complex, or outright impossible to create using traditional machining methods [1]. One such mechanism where additive manufacturing can play a pivotal role is in the development of reactor beds for monopropellant thrusters. The reactivity and stability of monopropellant reactor beds are the primary factors driving a thruster’s operational lifetime. State-of-the-art (SOTA) monopropellant reactor beds employ the use of granular catalysts, which degrade and shift over the thruster’s life. The degradation and shifting of granular catalysts results in a longer thrust rise time and increased chamber pressure oscillations. If these effects become too drastic, the thruster may no longer meet mission requirements and thus reach its operational end of life [2]. Additive manufacturing can offer technical solutions to replace and improve upon SOTA granular catalysts. Reactor beds which are additively manufactured can not only mitigate the issues of degradation and shifting plaguing SOTA granular catalysts, they can also be optimally designed for the various reaction stages taking place within the reactor. An optimized printed reactor bed has the potential to lead to better ignition characteristics, improved stability, a wider range of operational conditions, and increased lifetime. This solicitation seeks the development of an additively manufactured AF-M315E reactor bed for a 1N thruster. To maximize the likelihood of transition, the reactor bed should be optimized to provide an operational lifetime of approximately 40 hours and be capable of delivering a minimum impulse bit of 15mN-sec. 

PHASE I: Perform proof-of-concept analysis and experiments demonstrating the feasibility of the proposed reactor bed. Analysis and experiments should show practical manufacturability and performance/lifetime improvements over SOTA granular catalysts. 

PHASE II: Develop an additively manufactured reactor bed for a 1N AF-M315E thruster with the objective of achieving TRL 5 by the end of Phase II activities. 

PHASE III: Develop a 1N AF-M315E thruster incorporating the additively manufactured reactor developed under Phase II. 

REFERENCES: 

1. Beyer, S., “Hot Firing of World’s First 3D-Printed Platinum Thruster Chamber,” Airbus Defense & Space, ESA Space Engineering and Technology, June 15, 2015.; 2. McRight, Patrick, et al., "Confidence testing Of Shell-405 and S-405 Catalysts In a Monopropellant Hydrazine Thruster." 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 2005.

KEYWORDS: Spacecraft Propulsion, Chemical Propulsion, Additive Manufacturing, AF-M315E, Catalyst 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Future aircraft with high energy demands will have very high peak heat loads, current draws and fast transients. We need to develop innovative novel software tools/approaches. They are sought to manage electrical and thermal subsystems at platform level. 

DESCRIPTION: High energy airborne systems are expected to reach 150 kW (optical) within a few years. These systems will have peak electrical power draws in excess of 500 kW, peak thermal loads in excess of 400 kW and will be subject to fast transients at the beginning and end of a laser shot, as well as, in the middle of a laser shot. The lasers are expected to be laser diode pumped. The pump diodes themselves have very fast turn-on times while the electrical generation and heat removal systems have much slower turn on times. For overall energy efficiency, it is desired to have as low a quiescent power draw as possible. State-of-the-art high energy laser diodes are typically cooled below 30 degrees C (86 degrees F), this may change in the near future to 50 degrees C (122 degrees F) or higher. The successful proposal will develop software tools/systems capable of controlling electrical and thermal management subsystems subject to the timing of pumps, generators, valves, laser diodes, laser gain media, turrets and other components of airborne laser weapon systems to meet the operational demand signal. The proposal may discuss the Size, Weight, Power and Cost (SWaP-C) of components, sub-systems testing etc. These studies on new methods and technologies will have a good potential on improving the performance of commercial aircraft. 

PHASE I: It willl conduct a feasibility study and develop a high energy software control system capable of managing the electrical and thermal aspects of partner company's laser weapon system (LWS) model. The SBIR company will select a LWS model from an industry partner (weapon system contractor/engine companies, laser diode/laser source companies) and develop the software system capable of managing electrical and transient thermal challenges/issues. The SBIR company will participate in a workshop with stakeholders to insure requirements for prototype control system are clear. 

PHASE II: Itwill test the software control system on laboratory subscale prototypes or representative hardware to demonstrate successful platform – high energy system integration. Develop training manual and training plan to facilitate transition to the field. 

PHASE III: Demonstrate the Laser software control systems integration on a compatible aircraft platform. Provide training to stakeholders to accelerate transition to the field. Effort will complement an inital flight demo of high-powered laser pod on advanced tactical aircraft. 

REFERENCES: 

1. Hitzigrath, R., "Improving Aircraft Fuel-Thermal Management," SAE Technical Paper 932086, 1993, doi: 10.4271/932086.; 2. Gray, Charles N., and Shayeson, Maurice W., "Aircraft Fuel Heat Sink Utilization," https://apps.dtic.mil/dtic/tr/fulltext/u2/912902.pdf; 3. Karimi, Kamiar J., PhD, Senior Technical Fellow, "Future Aircraft Power Systems - Integration Challenges," Carnegie Mellon University Press, 2007.; 4. Swain, E.F., "Aircraft Avionics Cooling, Present and Future," Proceedings of the IEEE 1998 National Aerospace and Electronics Conference, 1998. NAECON 1998.

KEYWORDS: Propulsion, Power, Thermal Management, Laser, Directed Energy, Aircraft Heat Sinks, Low-Compatible, And Weapons 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop novel electrical connector and contact designs that offer reduced footprint and increased reliability and durability over standard electrical connectors used in harsh environments. 

DESCRIPTION: Electronic systems that operate in harsh environments are interconnected using a variety of circular and rectangular connector designs, often specified by MIL standards. They are a significant contributor to system upsets, both total and intermittent. State-of-the-art (SOTA) electrical connectors fail by combinations of opens (61 percent), shorts (16 percent), or intermittent connection (25 percent). Three basic mechanisms lead to failures that include, high cycle fatigue (HCF), tribology, and high temperature (over 150 degrees C). SOTA high density, high durability (1,500 cycles) connectors current packaging arrangements are large compared to the electronics volume. It is desirable to reduce the footprint of dense electrical signal connectors while also increasing the reliability and durability. In the SBIR Phase I effort, evaluation of novel mechanical configurations for both the connector and the contact should be accomplished, with the goal of volume reduction, high reliability, and compatibility with electronic fabrication applications. Approaches that increase the density of standard circular MIL DTL-38999, MIL DTL 5015, and related signal level (series I, II, III arrangement) connectors (1 -85 contacts) should be considered. Simulation of the major degradation mechanisms and understanding the challenges of defining test protocols should be considered. 

PHASE I: Develop an advanced high density reliable connector design with reduced size and improved cyclic durability and repeatable performance over the state of the art. The technology should be applicable to both legacy and advanced configurations for harsh environments. Demonstration of the prototype technologies capability should be accomplished through simulation and basic testing. Recommend the contractor work with appropriate industry partners with expertise in connector design, material science, fabrication, and reliability testing. 

PHASE II: Develop product like connector hardware components based on the Phase I prototype technologies selected. The hardware components electrical and mechanical capability will be demonstrated using appropriate test procedures for harsh environment applications. Suitability of the test procedures will be shown for the intended environments. Comparison of the technology with the state of the art will be accomplished. 

PHASE III: In Phase III, the ability to productionize the connector hardware for new and legacy systems will be developed. Cost effectiveness of the design will be assessed, and reliability and durability will be matured for military and commercial applications. Preliminary qualification issues will be addressed and performance of the connectors will be demonstrated on a ground test engine. 

REFERENCES: 

1. Mroczkowski, Robert S., “A Perspective on Connector Reliability”, Technical Presentation, 2004.; 2. Turck Connectivity, “Design Considerations For Harsh Environments”, White Paper, W1019, April 2017.; 3. Pascucci, Vincent C., “A Brief Overview of reliability in General and for Electrical Connectors in Particular”, July 1995.; 4. Arrowsmith, Peter., "Surface Mount Technology Association (SMTE)", “Electrical Connector Failure Investigation.”.

KEYWORDS: Electrical Connectors, Reliability, Harsh Environment, Contact Tribology, MIL Connectors, High Data Rate Connections 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop a novel strategy to increase the usable oil temperature of turbine engine oil pumps. Concepts focus to increase the usable temperature over conventional design to a temperature of 400-500 degrees F, while maintaining cold temperature requirements, -40 degrees F. The design should accommodate both MIL-PRF-7808 and MIL-PRF-23699 oil, and allocate the option of magnetic chip detectors and sensors. 

DESCRIPTION: Typical strategies for oil pumps will utilize oil supply pumping elements and air/oil scavenge elements. The oil pump design must also accommodate magnetic chip detectors, bypass valve and sensors. This SBIR topic seeks to explore new strategies/materials not currently utilized to increase the oil pump usable temperature to 400-500 degrees F, while maintaining a low temperature capability of -40 degrees F. A key focus would be a drop in replacement for legacy designs with significant usable temperature increase and no additional weight or complexity. A strong collaboration with the OEMs is highly recommended from Phase II of this program. 

PHASE I: Show the feasibility for a novel concept or new material for high temperature turbine engine oil pumps. Develop a design/test strategy for evaluating the ideas and identifying the key performance parameters necessary to document ability to perform on engine. Develop an initial transition and business plan. 

PHASE II: The methodology developed in Phase I should be validated for additional conditions approaching those found in practice with physical testing, and show feasible build processes and stable quality assurance processes. In the Phase II effort, steps should be taken to establish requirements for integration of the high temperature oil pump design into a standalone design tool that incorporates sufficient details to allow it to successfully predict increased performance. The work should be transitioned to interested OEMs. 

PHASE III: Future Phase III efforts should involve further commercialization of strategies developed for incorporation into elevated TRL demonstrations. These TRL demonstrations should focus on turbine engine lubrication system integration. Potential military application in NGAP, and a potential commercial application is the Boom Supersonic Transport XB-1 Aircraft for the SBIR/STTR technology. 

REFERENCES: 

1. MIL-PRF-7808 Specification; 2. MIL-PRF-23699 Specification; 3. MIL-PRF-87100 Specification (Cancelled, but may be of some help).

KEYWORDS: Oil Pump, Scaling, Retrofitting, MIL-PRF-7808, MIL-PRF-23699, Durability, Testing, Analysis 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop and demonstrate a low cost high altitude cold start ignition system for expendable small gas turbine engines. 

DESCRIPTION: The ignition environment of a gas turbine during high altitude (10,000 ft. to 35,000 ft.) air drop missions is very challenging. At the point of the drop, the pressure, temperature, and air mass flow are all low, and the entire gas turbine and fuel system are cold soaked to atmospheric temperatures (cold start). The ignition system has to light the combustor and spool up the engine to a self-sustaining condition over a finite period of time. For a given gas turbine and ignition system the resulting startup envelope is limited by Mach number, altitude, and environmental conditions as well as time from start of ignition to self-sustaining operation. Small engines are more challenging to ignite due to the constraints on the combustor design, primarily the high surface to volume ratio and low fuel flow injectors. The most common system utilized today is expensive pyrotechnic start cartridges. They result in fast spool up times and reliable high altitude starting with a wide startup envelop, but are expensive relative to the cost of the entire gas turbine and introduce handling, fragility, and aging issues. As the gas turbine decreases in size the percentage cost of the pyrotechnic start cartridge grows, representing almost 1/3rd of the entire cost of the system at the smallest scales. Commonly used lower power ignition systems, such as spark ignitors or glow plugs, have restrictive startup flight envelopes and long spool up times. This is very mission limiting due to the need for dive-to-start/climb to cruise mission profiles resulting in significant inefficiencies and longer times to target. It also decreases the survivability of the ordinance. Novel ignition approaches for the high altitude wing drop application are sought that result in a wide startup envelop, with a reasonable spool up time, and with reduced costs compared to existing approaches. Due to the nature of the mission, low cost is the most important attribute. The new approach must also be compatible with existing carriage resources and still meet the all operational requirements of the mission, such as carriage/launch loads of the system, thermal cycling, and long term storage. 

PHASE I: Create a preliminary design and show the feasibility of the novel ignition approach to achieve a wide startup envelop for a small engine in the air drop application. An initial estimate of the system’s weight, volume, viability to meet operational requirements, and the scalability of the approach should be included. Additionally, special attention should be made to estimate the resulting systems cost compared to current ignition approaches. 

PHASE II: Design, build, and test a prototype of the ignition approach developed in Phase I for a specific small gas turbine system in both a laboratory setting and in the gas turbine. It is recommended that collaboration with either a turbine engine manufacturer or a Government lab to perform the ignition test in the gas turbine. A vision system design should also be developed during Phase II. A refined estimate of the system cost and performance parameters should be made based on the vision system design. 

PHASE III: Develop a vision system level design for a specific existing expendable small gas turbine engine. Demonstrate/assess the startup envelop, spool up time, and projected final system cost. 

REFERENCES: 

1. “Comparative Analysis of Gas Turbine Engine Starting”, A. Beyene and T. Fredlund, American Society of Mechanical Engineers, 98-GT-419, (1998).; 2. "Gas Turbine Performance", P.P. Walsh and P. Fletcher, Chapter 9, Second Edition, Blackwell Science Ltd, Oxford UK (2004).; 3. "Experimental Investigations into High-Altitude Relight of a Gas Turbine", R.W. Read, Doctoral Thesis (2008).; 4. "Research on Windmill Starting Characteristics of MTE-D Micro Turbine Engine", Chen Xia, Xin Fu, Zhaoyun Wan, Guoping Huang, and Jie Chen, Chinese Journal of Aeronautics, Volume 26, Issue 4, Pages 858-867 (2013).

KEYWORDS: Low Cost, High Altitude, Cold, Start, Ignition, Expendable, Small Gas Turbine Engine 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop a system for integrated threat detection, classification, and situational awareness considering data associated with risk relative to assets, providing capability for fixed and mobile asset security leveraging all available information. 

DESCRIPTION: The USAF is tasked with securing both fixed-site facilities and mobile assets against a multiplicity of potential threats, including conventional weapons (rockets, artillery, mortars (RAM)), and shorter-range weapons (small arms, rocket-propelled grenades (RPGs)). Enemy use of vehicle-borne explosive devices and other improvised weapons are also of great concern. An emerging threat to site security is the rapid proliferation of low-cost UAS (“drones”). Weaponized drones, particularly operating in coordinated swarms, pose an immediate risk. Their low cost and commercial availability have enabled an increasingly deadly role in theater. Other threats include cyber-directed attacks against such infrastructure as the power grid or water supply. In some location, biological weapons, severe weather, wildfires, civil unrest, and many others threats can also pose significant operational hazards to secured facilities. Commanders are tasked with continually assessing these threats versus the risk associated with particular defended assets. This creates a feedback loop: assess the threat, evaluate the risk relative to affected asset(s), command the optimal response. Decision makers develop risk metrics—a product of the asset’s determined operational value, potential threats to that asset, and an assessment of its vulnerability. In reality, risk assessments continuously change, especially in light of detection and classification of threats constituting hostile intent. Presently, the nature of gathering and synthesizing data from a variety of sensor systems, each with its particular operating characteristics, requires operators to understand multiple disparate data streams from various systems. Under attack, interpreting these data streams requires an understanding of the “quirks” and characteristics inherent in each system. Decision making under such circumstances, especially if infused with incorrect and/or otherwise inaccurate information, may be suboptimal and thus prone to error. This project seeks to improve command responses by considering event detection data from multiple networks, paired with historical data, to update asset risk metrics in real time. Machine learning algorithms can be developed to aggregate these data and weigh relevant factors. In graphical terms, this can be visualized as a situational awareness display on which threat events are continually overlaid with an updating assessment of asset risk. This information can serve as an “automated playbook” on how best to respond to certain threats, and provide valuable insight to commanders and first responders faced with dispatching countermeasures in highly dynamic, and sometimes uncertain, tactical situations. This will enable faster response to attacks, and allow countermeasures to be directed more effectively. Overall, the payoff is better use of available USAF resources, and decreased logistical burden. This topic envisions utilization of emerging technologies in the realm of machine learning. Such systems are capable of improving their predictive accuracy (assessment of “truth”) as they are provided with more and more data. In the past few years, computational hardware required to utilize these tools has advanced to the point where such systems can be deployed in tactical command centers with minimal additional facilities requirements. Some of these systems utilize graphics processors (GPUs), which have been in wide circulation for about a decade. Additionally, new types of processor architectures are being developed specifically for deep learning frameworks. Coinciding with the advances in hardware, software tools are available that make development of applications readily accessible. 

PHASE I: It willdemonstrate the feasibility of an automated agent for situational awareness based on real-time determination of threat. Range and domain of threats and type of assets selected for assessment can be negotiated to pare the problem to a manageable level. Existing software systems may be utilized as needed. Final exam is a system simulation demonstrating one or more example scenarios. 

PHASE II: Deliver self-contained system capable of the objectives in a supervised setting integrated at a level suitable for demonstration. Implement algorithms based on historical and live data from three or more diverse sensors, at least one being from a mobile platform. The offeror shall attempt to quantify deviations in observed performance from that predicted in system simulations in Phase I. Deliverables shall include a functional real-time processor to be used in future testing and development. 

PHASE III: The system shall be further developed and improved based on results of earlier phases resulting in integrated tools ready for commercialization and transition to operational programs. This technology will provide a new and improved capability for First Responder centers in DoD, DHS, FAA, etc. 

REFERENCES: 

1. Girão P.S., Postolache O., Pereira J.M.D. (2009) Data Fusion, Decision-Making, and Risk Analysis: Mathematical Tools and Techniques. In: Pavese F., Forbes A. (eds) Data Modeling for Metrology and Testing in Measurement Science. Modeling and Simulation in Science, Engineering and Technology. Birkhäuser Boston.; 2. D.L. Hall and J. Llinas (Editors). Handbook of Multisensor Data Fusion. The Electrical Engineering and Applied Signal Processing Series, CRC Press LLC, Boca Raton (FL), 2001.; 3. Stampouli, D & Vincen, Daniel & Powell, Gavin. (2009). Situation assessment for a centralized intelligence fusion framework for emergency services. 2009 12th International Conference on Information Fusion, FUSION 2009. 179–186.; 4. https://developer.nvidia.com/deep-learning

KEYWORDS: Artificial Intelligence, Big Data, Data Analytics, Data Fusion, Machine Learning, Risk Analysis 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Environmentally benign material that rapidly collapses foam, is non-injurious to military assets or personnel, and cleans up with foam after a release event; delivery system for said composition must integrate with the hi-EX foam sprayer system. 

DESCRIPTION: Accidental Hi-EX foam releases in hangars have killed and injured personnel. In 2014 an accidental release of foam killed two contractors at Eglin AFB, FL. Hi-EX foam is necessary to put our hangar fires, as there is no practicable substitute currently on the market to replace it for hydrocarbon fires. Therefore, there is need for a technology that rapidly (20 or more feet of foam within 3 minutes) collapses the foam without damaging military assets or poisoning personnel, is environmentally friendly (i.e. biodegradable, non-persistent in the environment, and non-toxic) and is easy to clean up. The current state-of-the-art is to spray the foam with water to dissipate it, or waiting for the foam to break down on its own. Each is unacceptably slow. The delivery system for this material must be compatible with current technology. Hi-Ex foam is generated in specialized systems that are so deployed as to evenly cover the hangar with foam when deployed. The delivery system of the chemical should 1) also evenly cover the hangar, to evenly collapse the foam when deployed, and 2) not interfere with the working of the Hi-Ex foam system or other hangar systems. 

PHASE I: Sample of material that collapses a column of Hi-EX foam at mean rate NLT 6 ft/min. Apply agent to Hi-EX foam from bench-scale prototype delivery system. For any component not known to be environmentally benign, offeror shall provide lab data (e.g., LD50, IC25, BOD, COD, environmental persistence and breakdown products, etc) identifying potential environmental impact of material. Corrosivity or other degradation of typical hangar materiel or staff is unacceptable. 

PHASE II: Assemble and demonstrate a full-size prototype delivery system in a hangar-sized area at Tyndall AFB. Collapse 20 ft of Hi-EX foam in a volume the size of an F-35 hangar in three minutes or less. The foam and chemical remnants should be no more difficult to clean up than a spontaneously collapsed foam 

PHASE III: Market Final product to civil and private aviation for aircraft hangar fire suppression, flammable storage facilities, and emergency management areas. 

REFERENCES: 

1. Weaver, R. “Commander Directed Investigation Findings and Conclusions Concerning Eglin AFB Accidental High Expansion Foam Discharge and Fatality,” Eglin Air Force Base, Florida (undated.); 2. NFPA 409, Standard on Aircraft Hangars; 3. NFPA 11 A, Standard for Medium- and High-Expansion Foam Systems

KEYWORDS: Hi-Ex Foam, High Expansion Foam, Hangar, Aircraft 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: An autonomous system to identify, assess, respond to, and suppress or extinguish an aircraft fire within 10 miles of the stationed unit and conduct rescue. 

DESCRIPTION: Unmanned and autonomous systems technology has burgeoned for more than a decade, outpacing methods to apply the capabilities to applicable problems. Technology is sought that autonomously gathers and processes information from various sources and sensors to identify an aircraft fire, communicate with other aircraft traffic and initially respond to an aircraft fire autonomously. During an event, the system will notify emergency services, deploy and using the Unmanned Aircraft System Traffic Management System (UTM) or similar system navigate through military and civilian airspace to an aircraft fire while carrying the means to suppress or extinguish a 50-MW fire and conduct a basic rescue mission on conscious personnel. The minimum payload the system should be able to carry is 1 metric ton to successfully perform the firefighting and rescue mission. Relevant state-of-the-art robotic firefighting technology ranges from tethered drones to heavy lift semi-autonomous aircraft. Solutions are sought that provide a semi-autonomous, non-tethered response to aircraft fire events in the vicinity of airbases and airfields. The solution should be able to operate close to a 50-MW fire without degradation. The system should be able to stay on station for the minimum estimated response time of the local emergency services. A highly desirable feature would be ability to map the trajectory of an aircraft making a mayday call to estimate point and time of impact, to allow an extinguishment response before the fire has developed. The same constraints on toxicity, environmental persistence, etc. apply as to AFFF replacements. 

PHASE I: Use small-scale, virtual or modeling & simulation testing & evaluation to identify possible solutions and develop initial software for fire and emergency identification and communication with emergency services. Demonstrate detection & control functions with a small drone. Justify the choice of extinguishant. 

PHASE II: Assemble a prototype system for field demonstration in a relevant operating environment selected with service input. After the demo deliver the system to the Government for end-user evaluation. The prototype must autonomously deploy and navigate to an aircraft fire while communicating relevant information to aircraft control systems. 

PHASE III: Final product will find a market in civilian and private aviation, firefighting and emergency management areas. 

REFERENCES: 

1. FAA Circular 150/5200-31C- Airport Emergency Plan (Consolidated AC includes Change 2) June 19, 2009; 2. NFPA 403 Standard for Aircraft Rescue and Fire-Fighting Services at Airports, 2018; 3. Stalker and K-MAX talk to air traffic control to safely operate while detecting and dousing fires, 7 DEC 2015, https://spectrum.ieee.org/automaton/robotics/drones/lockheeds-drones-fires

KEYWORDS: Aircraft Rescue And Firefighting (ARFF), Autonomous, Drone, Extraction 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a small multi-spectral imagery pod, to hang under a drone or attached to a rover, capable of providing data to show high resolution vegetation health and distribution, soil properties, soil density, moisture content, etc. to include the “biological soil crust” to assist in restoration efforts and collect data required to comply with the Endangered Species Act (ESA) and the Sikes Act, that would otherwise require “boots on the ground”. 

DESCRIPTION: Vegetation health is a determinate parameter in the management of wildlife. This effort will address the relative heath of vegetation to include the “biological soil crust” and provide data for management activities (e.g. recovery and revegetation). Plants appear green because chlorophyll in the leaves absorbs much of the incident light in the visible wavelengths, particularly the blue and red, while the green color is reflected. Therefore, light reflected by the leaves depends on the amount and various types of leaf pigments that can be used to predict relative health. For example, a water-stressed leaf is known to have low reflectance in the nonvisible wavelengths from about 750 to 1100 nm. Measuring the difference in reflected light at various wavelengths of the electro-magnetic spectrum also makes it possible to distinguish vegetation from soil, green and senescent vegetation, and vegetation species. There has, however, been limited to no application of this technique to rangeland management or to the microbiotic crusts management. Multi-spectral imagery has been widely used to assess crop condition, cover, and growth. Different crop characteristic can be determined based on the band combinations used and include chlorophyll content, biomass and water stress. Hyperspectral imaging is also being used in the detection and diagnostics of disease, nutrient deficiencies, weeds and pests in crop fields. Soil crusts are formed by living organisms and their by-products, creating a surface crust of soil particles bound together by organic materials. Aboveground crust thickness can reach up to 10 cm. The general appearance of the crusts in terms of color, surface topography, and surficial coverage varies. Soil crusts play an important role in the environment. Because they are concentrated in the top 1 to 4 mm of soil, they primarily effect processes that occur at the land surface or soil-air interface. These include soil stability and erosion, atmospheric nitrogen-fixation, nutrient contributions to plants, soil-plant-water relations, infiltration, seedling germination, and plant growth. Crusts are well adapted to severe growing conditions, but poorly adapted to disturbances. Domestic livestock grazing, and more recently, recreational activities and military activities place a heavy toll on the integrity of the crusts. Disruption of the crusts brings decreased organism diversity, soil nutrients, stability, and organic matter. Fire is a common occurrence in many regions where microbiotic crusts grow. Investigations show that fires can cause severe damage, but that recovery is possible. Low-intensity fires do not remove all of the crust structure, which allows for regrowth without significant soil loss. Shrub presence increases the intensity of the fire, decreasing the likelihood of early vegetative or crust recovery. Full recovery of crust from disturbance is a slow process, particularly for mosses and lichens. There are, however, means to facilitate recovery if the location of viable communities can be determined. The proposed technology should be man portable, attached to a rover or drone. The system cannot rely on grid transmitters or receivers and must be appropriate for use in federally designated critical habitat. This is not a request for a drone or rover development. The sensor pod should be self-contained and of a size suitable for use on a drone or rover. 

PHASE I: Research in this phase should focus on device stability in rough terrain to prevent device tip over, bandwidth constraints for operation of the vehicle and camera resolution, battery life/recharging- current batteries require fairly frequent recharging and the method of delivering electricity to the vehicle – i.e. prove of concept. 

PHASE II: It should be focused on system design, manufacturing, environmental maintenance, and quantification of system performance of a pre-production prototype. From the applied research and conceptual design in Phase I, develop a working, scaled- up prototype system. Evaluate if the system can determine the health of vegetation and soil crusts. 

PHASE III: Military Application: Military bases are required by the Sikes Act to manage the wildlife on their bases. Historically, this data has been collected by “boots on the ground” biologist. Field biologist are expensive and sometime difficult to find to provide the data need to comply with the various federal wildlife related laws (ESA, Sikes Act, etc.). Commercial Application: All federal and state agencies that manage land are required by various laws and regulations to manage the wildlife on their land. As on military land, this data has been historically collected by “boots on the ground” biologist. With reduce budgets and limited manpower these agencies must still comply with the various federal wildlife related laws 

REFERENCES: 

1. Carter GA, Knapp AK (2001) Leaf optical properties in higher plants: linking spectral characteristics to stress and chlorophyll concentration. Am J Bot 88:677–684; 2. Du Q, French JV, Skaria M, Yang C, Everitt JH (2004) Citrus pest stress monitoring using airborne hyperspectral imagery. In: Conference Proceedings of the International Geoscience and Remote Sensing Symposia 2004, edited by IEEE (Anchorage, USA), Vol. VI, 3981–3984; 3. Jacobi J, Kühbauch W (2005) Site-specific identification of fungal infection and nitrogen deficiency in wheat crop using remote sensing. In: Proceedings of the 5th European Conference on Precision Agriculture, edited by J.V. Stafford (Wageningen Academic Publishers, Netherlands), 73–80

KEYWORDS: Vegetation Health, Multi-Spectral Imagery, Sensor, Detection, Critical Habitat, Federally Threatened Species 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a real-time peak shaving, energy storage technology that can be installed at an AF sustainment complex / industrial facility. 

DESCRIPTION: Because electricity pricing is tied to usage, power consumption during peak times costs considerably more than power purchased during off-peak time. The focus of this effort is to develop cost-efficient energy storage solutions. Storage would be filled with off-peak power (or potentially alternative power) and fed back into the system during peak usage. The solution would also require real time usage monitoring system in order to predict when to charge and when to discharge. Determine acceptable locations and size for energy storage integration within the installation’s electric distribution system. This effort will be coordinated with a utility privatization contractor - privately owned power management company (City Light and Power (CLP)) and the base Civil Engineering. CLP maintains and operates the military installation’s transmission and distribution systems. The main base power at Hill reaches peak demand around 45 megawatts (MW). Peak demand during summer months usually occurs between 1 p.m. and 2 p.m. Monday through Thursday. Rocky Mountain Power (RMP) supplies electricity to Hill under rate schedule 9. During summer months, RMP Rate 9 on-peak hours begin at 1 p.m. and end at 9 p.m., Monday through Friday. Summer peak power charge is $13.96/kW and there is no power charge for off peak hours. Winter on peak hours begin at 7 a.m. and end at 11 p.m., Monday through Friday. Winter peak demand usually occurs around the 10 a.m. hour Monday through Thursday, peak charges are $9.47/kW with no power charge for off peak hours. RMP supplies power at 46 kV to HAFB. Power is supplied to substation 5 from the south side of the base through the Syracuse substation switch (SSS) located near the Fam Camp within the base fence line. 46 kV power is stepped down to 12,470 V at substations 2, 3, 4 and 5. Backup feed is at substation 2 during SSS interruption. Service to substation 2 is fed from the RMP Riverdale substation. Substation 2 is located on the north side of the base, 10 miles away from substation 5. The SSS switch serves as the line of demarcation between RMP and CLP distribution assets. Time meter data can be obtained at the SSS, current meter data is delivered to HAFB by RMP with a 24 hr delay. Real time metering of 1 to 15 min. could be sent to the base advanced metering reading system (AMRS) if appropriate cyber security authorization is obtained. Integrating with AMRS would allow user interface with the meter data. The system shall determine when power should be applied to or drawn from the storage device. This effort shall shave the peak load demand for power from the utility company. R&D controls shall ensure safe energy discharge into and off of the transmission system. At a minimum the system shall provide 1MW to 2 MW of peak shaving – greater values will be considered. The R&D shall optimize the energy storage, charge and discharge rates. The algorithm for energy discharge shall be based on demand profile, rate 9 on-peak schedule and real time data acquisition. The contractor shall develop the appropriate power metering, data acquisition and communication infrastructure. The contractor shall determine the best energy storage technology option (could be combination of energy storage techniques) for the AF sustainment installation. 

PHASE I: R&D solution that meets the above requirements and conduct preliminary business case analysis (BCA) to determine implementation costs, including a return-on-investment (ROI) calculation that compares anticipated savings to expected costs. Proof-of-concept prototype(s) shall be developed to demonstrate conformance to the requirements. 

PHASE II: Initiate and complete the test plan developed in Phase I. Proof-of-concept prototype(s) shall be refined to installation-ready article and shall undergo testing to verify and validate all requirements. This process may require multiple iterations before a final design is selected. Refine BCA/ROI based on the final design. 

PHASE III: If developed technologies are cost effective, passes verification / validation and qualification testing, then it shall proceed to transitioning and implementation of the technologies. With possible application to other AFSC sites. 

REFERENCES: 

1. Department of Defense 2016 Operational Energy Strategy; 2. Department of Defense Energy Manager’s Handbook, Aug 5 2005; 3. Department of Defense Directive Number 4180.01 16 Apr, 2014; 4. Air Force Policy Directive (AFPD) 90-17, Energy and Water Management, 18 Nov 2016

KEYWORDS: Facility Power, Peak Shavings, Energy Storage, Electric Power 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Determine threshold of finite element analysis “hot spot” characteristics where real-world degradation or failure effects become predictable and measureable. 

DESCRIPTION: Hill AFB Landing Gear (LG) office uses Finite Element Analysis (FEA) to predict LG part failures. Analyses will often reveal localized stress concentrations or “hot spots” where a limited number of elements are indicated by the software as exceeding material limits. Currently, determination as to when the hot spots would result in real-world part failure is based on the size of the area of elements stressed above yield or ultimate strength. This determination is subjectively based on the experience of the LG engineer performing the FEA, and can differ between engineers even for the same component in the same situation. For example, some have used the criteria in industry boiler and pressure vessel standard ASME BPVC Section VIII-2 to make this determination for LG hardware. The research and development effort shall produce a predictive relationship between FEA stress concentration characteristics and real-world hardware effects under the same loading conditions. Relevant characteristics of FEA hot spots may include but are not limited to mesh or part geometry, size, stress levels, location, distance between stress concentrations, and sensitivity to existing part defects/damage. Loading scenarios may include tension, compression, shear, and bending. Common LG part materials include Aluminum 7075-T73 and 7050-T73, Steel 300M and 4340. Alternative finite element software/meshing/analysis methods other than what Hill AFB currently uses are within scope of this study. The model predictions shall be verified and validated on physical test specimens according to ASTM E8 for tension. The contractor shall publish a commercial standard or specification for interpreting FEA stress concentrations based on the results of this effort. 

PHASE I: R&D solution that meets the above requirements and conduct preliminary business case analysis (BCA) to determine implementation costs, including a return-on-investment (ROI) calculation that compares anticipated savings to expected costs. Proof-of-concept prototype(s) shall be developed to demonstrate conformance to the requirements. 

PHASE II: Initiate and complete the test plan developed in Phase I. Proof-of-concept prototype(s) shall be refined to installation-ready article and shall undergo testing to verify and validate all requirements. This process may require multiple iterations before a final design is selected. Refine BCA/ROI based on the final design. 

PHASE III: If developed technologies are cost effective, passes verification / validation and qualification testing, then it shall proceed to transitioning and implementation of the technologies. With possible application to other AFSC sites. 

REFERENCES: 

1. ASME/BPVC sec VIII-2 "Boiler and Pressure Vessel Code (BPVC)"; 2. ASTM E 8 "Standard Test Methods for Tension Testing of Metallic Materials"; 3. “The Theory of Material Failure” By Richard M Christensen ISBN # (978-0-19-966211-1)

KEYWORDS: Finite Element Analysis, FEA, Hotspots, Landing Gear 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: R&D an ergonomic dead man switch design for use with Hill AFB PMB equipment 

DESCRIPTION: Abrasive blast operators within 576 PSS need an ergonomic replacement for the blast activation dead man switch currently used on plastic media blast (PMB) nozzles for paint removal on F-16, C-130, and A-10 aircraft. Currently, PMB operators activate hoses by squeezing a large dead-man switch affixed to the PMB nozzle. The grip forces required to initiate and maintain trigger activation are 16-lbf and 8-lbf, respectively. Pre-activation and activation tangential grip distances are 3.75-in and 3-in, respectively. PMB operators can be expected to hold these trigger grips in activated position for up to four hours per shift. Due to the poor ergonomic qualities of the current switch, 576 PSS operators experience abnormally high rates of chronic shoulder injuries and carpal-tunnel syndrome (CTS) corrective surgeries costing the Air Force an estimated $340,000 per year in workman’s compensation, operator time off-work, or alternate work assignments. The replacement design must meet OSHA dead man switch requirements and reduce or eliminate the fatigue and injuries associated with the current switches. The design shall meet performance, interface, and form-factor requirements of 576 PSS’s PMB systems. To reduce the risk of CTS and shoulder injuries, the design shall meet or exceed requirements in OSHA Standard 1910.244(b) and its two accompanying interpretations, and MIL-STD-1472G. The maximum allowable activation and maintaining grip pressures shall be 5-lbf and 3-lbf respectively. The design shall be adjustable, to provide ergonomic benefit regardless of the individual operator using it, and shall not exceed 12 oz. in weight. The design shall be equally useable by operators lying prone in F-16 intakes and by users standing up straight. Maximum switch deactivation time shall be 0.3 seconds. The switch shall be designed to mitigate risks to the aircraft being worked on, primarily that of contact damage. The switch shall survive 100 repeated 48-in vertical drops onto concrete in its operational configuration and remain functional for at least 500 hours of cumulative use. The design shall be resistant to un-commanded activation through drops, bumps, or electromagnetic interference (EMI). The design, when engaged and allowing flow of media, shall reliably disengage in 0.5-sec or less to de-activate media flow in user-unconscious, nozzle-drop, and other physical failure scenarios. The design shall interface with 576 PSS’s pneumatically controlled PMB systems, and shall be able to be exchanged from the blasting hose in under 6 minutes using common tools. The design must be self-contained (i.e. no interface to systems other than the user and PMB system), and shall not interfere with the operator’s personal protective equipment (PPE), stands, or equipment. The allowable physical envelope for the design is within 5 inches radially from the blast hose, with at least 2 inches of clearance from the opening of the blast nozzle, and length not to exceed 8 inches. The design shall meet or exceed OSHA requirements for equipment used in Class II Division 1 locations. 

PHASE I: R&D solution that meets the above requirements and conduct preliminary business case analysis (BCA) to determine implementation costs, including a return-on-investment (ROI) calculation that compares anticipated savings to expected costs. Proof-of-concept prototype(s) shall be developed to demonstrate conformance to the requirements. 

PHASE II: Initiate and complete the test plan developed in Phase I. Proof-of-concept prototype(s) shall be refined to installation-ready article and shall undergo testing to verify and validate all requirements. This process may require multiple iterations before a final design is selected. Refine BCA/ROI based on the final design. 

PHASE III: If developed technologies are cost effective, passes verification / validation and qualification testing, then it shall proceed to transitioning and implementation of the technologies. With possible application to other AFSC sites. 

REFERENCES: 

1. OSHA Standard 1910.244(b) – Occupational Safety and Health Standards; 2. MIL-STD-1472G – Human Engineering; 3. OSHA Standard 1926.449 – Safety and Health Regulations for Construction

KEYWORDS: Ergonomic, Bead Blast, Fatigue, Safety, Carpal Tunnel, Chronic Shoulder Injuries, Trigger Grip 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a MIL-PRF-85285 topcoat capable, high accuracy spray head to allow for the implementation of robotic stenciling/painting capabilities of aircraft markings. 

DESCRIPTION: Repaired aircraft parts must be repainted prior to reinstallation, and marked in accordance with T.O. 1-1-8, per AFMCI 21-117. The 402nd CMXG at Robins AFB currently utilizes robotic technologies in their repainting processes. However, the application of markings using stencils continues to be conducted by hand as the spray head used to paint large areas are not capable of fine, high accuracy swaths. An opportunity exists to automate the application of aircraft markings, creating a robust, efficient process absent of reiteration due to human error. Currently, technology exists allowing for the automated painting and marking of aircraft parts using patented hardware and software for “large -scale robotic inkjet printing on aircraft and other complex surfaces”1. Southwest Research Institute (SwRI) was awarded a patent for “High Accuracy Inkjet Printing,” in which ink is “printed” onto complex surfaces, such as aircraft parts, with high precision. However, the ink utilized in this process is not equivalent to the MIL-PRF-85285 topcoat required for aircraft markings in accordance with T.O. 1-1-8, per AFMCI 21-117. Furthermore, the hardware is not capable of spraying the more viscous MIL-PRF-85285 topcoat. The proposed research would consider the existing “Inkjet Printing” technology to design and develop a high accuracy, controlled-spray paint head capable of the “precise application of multiple graphic swaths of color MIL-PRF-85285 topcoat onto complex surfaces, creating a contiguous graphic image”2. The development of high accuracy topcoat “printing” will alleviate discontinues, spaces, gaps, and other human errors that result in the need for reiteration on an already time consuming process. Additionally, the development of such capabilities will expedite the painting and marking process, removing it as a bottleneck of the repair and reinstallation procedures. 

PHASE I: Develop a proof of concept high accuracy “Paint Jet” prototype. In this phase, the process will demonstrate ability to produce a controlled spray of MIL-PRF-85285 topcoat. Precise application, or “Printing”, of multiple swaths of color topcoat may be limited to flat surfaces in a single direction of movement. The prototyping in this phase will provide key input to developing the capability to create a contiguous encoded pattern over complex surfaces. 

PHASE II: Develop the high accuracy “Paint Jet” to a deployment ready state. Greater ability to “print” MIL-PRF-85285 topcoat over complex surfaces will be implemented. The “Paint Jet” head will be fit to the 402nd CMXG’s robots, and timed with their system to ensure the accurate and precise application of multiple swaths of color paint creating contiguous graphic images. The goal of the phase II will be working robotic stencil/marking capabilities resulting in measurable improvements in the processing time of repainting and marking repaired aircraft parts. 

PHASE III: A successful system could be marketed to other defense customers who require the ability to quickly apply markings using high resilience paint, such as MIL-PRF-85285 topcoat. 

REFERENCES: 

1. Evans, Paul. “Blazing a Trail for Smarter, More Agile Automation”, Industry Today, Vol. 20, Issue 1, March 2017.; 2. “Patented SwRI Inkjet System Can Literally Ink a Jet”, Southwest Research Institute, https://www.swri.org/press-release/patented-swri-inkjet-system-can-literally-ink-jet, 28 February 2017.; 3. “Corrosion Control and Prevention Program and Marking of Aerospace Equipment”, Air Force Materiel Command Instruction 21-117, http://static.e-publishing.af.mil/production/ 1/afmc/publication/afmci 21-117/afmci21-117.pdf, 28 May 2014.; 4. “Application and Removal of Organic Coatings, Aerospace and non-Aerospace Equipment”, Technical Manual: TO 1-1-8, http://www.robins.af.mil/Portals/59/document s/technicalorders/1-1-8.pdf?ver=2016-07-29-154634-250, 24 August 2017.

KEYWORDS: Stencil, Automated, Spray 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Research and develop a technology capable of generating high precision point cloud scans of intricate parts with multiple internal services that are not accessible for traditional laser scanning or other line-of-sight techniques. 

DESCRIPTION: Many gun systems in armament require intricate castings of aluminum or steel parts with multiple internal surfaces that are very difficult to inspect with traditional means and impossible to inspect with line of sight surface scanning such as laser scanning. This makes it extremely difficult and time consuming to inspect these parts during first article testing or production lot testing which adds to lead time and risk associated with procurement. It also makes government testing of failed parts nearly impossible because of the lack of specialized tooling and fixtures to hold/check the parts. A technology is being sought that has the ability to look through the part (similar to an X-ray) and generate a very precise point cloud or surface model of the part. This point cloud or model must be accurate down to 0.0001-inch objective, 0.0005-inch threshold for the entire part. The technology must be capable of working through any steel or aluminum with a wall thickness of approximately 0.5 inches. The operation should be as automated as possible and require very little user training. The bounding box for most parts is 18 in. x 18 in. x18 in. or less, though some parts would require a larger capacity of approximately 24 in. x 24 in. x 36 in. Current scanning inspection techniques are limited to surface laser scans. There are some rudimentary X-ray inspection techniques, but these are mostly limited to visualization and flaw detection. There is currently no technology that can measure, visualize, and display non-line-of-sight dimensions, though it may be possible to marry current line-of-sight scanning with X-ray or other non-destructive inspection techniques. 

PHASE I: Demonstrate hidden surface scan feasibility and develop a complete a demonstration of concept for accurately measuring non-line-of-sight dimensions. 

PHASE II: Demonstrate a full scan of a moderately complex casting up to 18 in. x 18 in. x18 in., with internal dimensions accurately measured, tolerance, and displayed. 

PHASE III: Demonstrate a full scan of a complex casting up to 18 in. x 18 in. x18 in., with internal dimensions accurately measured, tolerance, and displayed. 

REFERENCES: 

1. J.E. Goodman, J.O'Rourke, editors \Handbook of discrete and computattional geometry," CRC Press LLC, Boca Raton, FL; Second Edition, April 2004.; 2. S. Sachs, S. Rajko, S.M. LaValle \Visibility based pursuit-evasion in an unknown planar environment," to appear in International Journal of Robotics Research, (2003).; 3. Validation of a Non-Line-of-Sight Path-Loss Model for V2V Communications at Street Intersections, Abbas, Taimoor; Thiel, Andreas; Zemen, Thomas; F. Mecklenbräuker, Christoph; Tufvesson, Fredrik

KEYWORDS: Point Cloud, Non-line-of-sight Dimensions 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a robust, solid-state, scalable all-electronic switching and broadband amplification technology that operates in the >10 THz regime at 10+6 A/cm2 current densities with a 1W output power. 

DESCRIPTION: An electronic technology platform for the broadband amplification of currents at speeds up to 30 THz with ideally symmetric on-off characteristics and sufficient power of 1 W is needed. High frequency, high power amplifiers are currently bottlenecks for many technologies including satellite communications, remote sensing and threat detection, or electronic warfare [1], but especially for radar such as on combat aircraft [2]and ultra-high frequency telecommunications with extreme bandwidth in the atmospheric attenuation window [3, 4] around 30 THz. For such applications, additional requirements for this technology include stability over a very wide operating temperature range. This topic calls for new solid-state device architectures based on new materials because of the limitations of existing technologies. All practical broadband amplifiers that operate at >1 THz are based on the more than one-hundred year old principle of vacuum tubes. However, pushing vacuum electronics significantly above THz frequencies requires significant advances in nearly all aspects, including novel ultra-high precision manufacturing, designs for ultra-high current density electron beams, new cathode materials, novel circuit designs and optics [1]. This complexity makes solid-state devices highly desirable. However, solid-state devices based on semiconductor materials are fundamentally limited in speed by the capacitance of the depletion layers inherent in all junction-based devices. The depletion layers in diodes and transistors form capacitors and the required capacitor charging and especially discharging (“off-switching”) during transistor switching limits the maximum operating frequency. Metal-insulator-metal junctions also have inherent capacitances. Besides, demonstrated power output is in the W – few-mW range, and unpractical cryogenic cooling is typically required. Spin-based transistors have been previously pursued but their operating speeds are limited by the ferromagnetic resonance frequency [5]. The theoretical scaling relation Power 1/(frequency)2 [6] limits all technologies except for vacuum electronics to lower power than the 100 mW to 1 W needed for useful telecommunication [1]. Because of these reasons, a solid-state based broadband amplification technology is solicited with key performance parameters of 30 THz, frequency, power output of at least 1 W, and operating temperatures over a wide range, significantly above room temperature. 

PHASE I: Develop a conceptual design of a broadband, all solid-state gain-achieving device working up to 30 THz, with at least 1 W output power, and current densities of 106 A/cm2. The development will be based on an analysis of existing materials, identify the high-risk technical elements, and initial risk reduction via testing or modeling. Demonstrate the feasibility of this fundamental approach. Narrow achievable device parameters in terms of gain frequency and power response. 

PHASE II: Demonstrate gain in a real device. Demonstrate fanout. Build one prototype device that can achieve the specifications. Establish the device geometries and material properties that are most critical to achieve a large current gain and the frequency response. Optimize materials to maximize gain at frequencies > 10 THz. 

PHASE III: Commercialize electronics switching platform. Expand the capability to meet requirements for other Air Force test facilities and mature the technology for commercialization to all DoD facilities and the private sector. 

REFERENCES: 

1: S.S. Dhillon, M.S. Vitiello, E.H. Linfield, A.G. Davies, C.H. Matthias, B. John, P. Claudio, M. Gensch, P. Weightman, G.P. Williams, E. Castro-Camus, D.R.S. Cumming, F. Simoens, I. Escorcia-Carranza, J. Grant, L. Stepan, K.-G. Makoto, K. Kuniaki, K. Martin, A.S. Charles, L.C. Tyler, H. Rupert, A.G. Markelz, Z.D. Taylor, P.W. Vincent, J.A. Zeitler, S. Juraj, M.K. Timothy, B. Ellison, S. Rea, P. Goldsmith, B.C. Ken, A. Roger, D. Pardo, P.G. Huggard, V. Krozer, S. Haymen, F. Martyn, R. Cyril, S. Alwyn, S. Andreas, N. Mira, R. Nick, C. Roland, E.C. John, B.J. Michael, The 2017 terahertz science and technology roadmap, Journal of Physics D: Applied Physics 50(4) (2017) 043001.

2:  T. Withington, Chinese Claims of Terahertz Radar? https://www.monch.com/mpg/news/ew-c4i-channel/3881-chinesewhispers.html, 2018 (accessed 12/18/2018.2018).

3:  G.J. Zissis, W.L. Wolfe, The infrared handbook, Infrared Information and Analysis (IRIA) Center for the Office of Naval Research, Washington, 1978.

4:  S. Hakusui, Fixed Wireless Communications at 60GHz Unique Oxygen Absorption Properties. 2001 (accessed 12/18/2018.2018). [5] M. Johnson, Bipolar spin switch, Science 260(5106) (1993) 320-3. [6] J.H. Booske, Plasma physics and related challenges of millime

KEYWORDS: THz Electronics, All-electronics Circuits 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: This is an AF Special Topic in partnership with AFWERX, please see the above AF Special Topic instructions for further details. A Phase II may be awarded for a maximum period of 15 months and $750K. The objective of this topic is to explore Innovative Defense-Related Dual-Purpose Technologies that may not be covered by any other specific SBIR topic and thus to explore options for solutions that may fall outside the Air Force’s current fields of focus but that may be useful to the US Air Force. This topic will reach companies that can complete a feasibility study and prototype validated concepts in an accelerated II schedule. This topic is specifically aimed at later stage development rather than earlier stage basic science and research. 

DESCRIPTION: The Air Force is a large and complex organizations that consists of many functions that have similar counterparts in the commercial sector. We are interested in exploring innovative technology domains that have demonstrated clear commercial value in the non-defense sector (i.e., through existing products/solutions) in order to see if they have similar Air Force applications (i.e. Dual-Purpose Technologies/Solutions). We recognize that it is impossible to cover every technological area with the SBIR topics, thus this topic is intended to be a call for open ideas and technologies that cover topics that may not be currently listed (i.e. the unknown-unknown). It is important that any potential solutions have a high probability of keeping pace with the technological change and thus should be closely tied to commercial technologies and solutions that will help support the development of the solution. This topic is meant for innovative non-defense commercial solutions to be adapted in innovative ways to meet DoD stakeholders’ needs in a short timeframe and at a low cost. Solutions for this topic should be focused on the three areas listed below and should try to meet as many of these as possible. 1. Technical feasibility – There should be minimal technical risk to the overall solution. The best solutions will have demonstrated technical feasibility by showing the solution being used broadly by other customers, especially in the non-defense space. 2. Financial Sustainability – The offeror(s) should demonstrate financial sustainability of the solution and the offerer(s). The best solutions will demonstrate this by sales of the solution to non-defense clients and other sources of private investment. 3. Defense Need – The offerer(s) should demonstrate that they have an understanding of the fit between their solution and defense stakeholders. The best solutions will demonstrate this with documentation (i.e. a signed memo) from a specific, empowered end-user and customer (the end-user and customer may not be the same person) in the USAF who is ready and willing to participate in the trial of the proposed prototype solution. This should include specific objectives and measureable (quantitative) key results that the proposed solution can achieve to meet the needs of the AF end-user and customer. In summary - proposals for this topic should demonstrate a product-market fit between an Air Force end-user and the proposed adaptation of an existing non-defense commercial solution. This can be done through a proposal with a mature non-defense technical solution with a clear understanding of how it can be adapted to meet the specific needs of an Air Force Customer along with documentation from a specific motivated and empowered AF end-user and customer who is ready and willing to participate in the trial of the proposed prototype solution. AREAS OF FOCUSED DEFENSE NEED FOR 19.2 OPEN TOPIC For this round of special topics, we have noticed a significant amount of potential AF defense end-users with interest in the topics listed below, meaning that if your solution can help address these problem areas, there are likely to be a good number of AF End-Users and customers that you can interact with in your phase II implementation. If you believe your solution can help address one of the focused defense needs, please note this in your application slide deck. Note that this does not change the requirement to demonstrate the defense need as listed above. This also does not preclude companies who are looking to solve other problems to submit to this topic, it is simply intended to give indications of areas of special focus for the Air Force at this particular point in time. Link to Focus Areas: https://www.afwerx.af.mil/sbir.html NOTES: a. Due to the large amount of expected interest in this topic, we will not be answering individual questions through e-mail, except in rare cases. Instead we will be holding a teleconference to address all questions in an efficient manner. This topic will be updated with the final call-in details as soon as the date is finalized. In the meantime, feel free to use the SITIS Q&A system. b. This SBIR is NOT awarding grants, and is awarding contracts, when registering in SAM.gov, be sure to select ‘YES’ to the question ‘Do you wish to bid on contracts?’ in order to be able to compete for this SBIR topic. If you are only registered to compete for grants, you will be ineligible for this topic. For more information please visit http://afwerxdc.org/sbir/ c. We are working to move fast, please double check your CAGE codes and DUNS numbers to be sure they line up, if they are not correct at time of submission, you will be ineligible for this topic. In order to ensure this, please include, in your 15-slide deck, a screenshot from SAM.gov as validation of your correct CAGE code, DUNS number and current business address along with the verification that you are registered to compete for All Contracts. For more information please visit http://afwerxdc.org/sbir/ d. In order to keep pace with the fast timeline, if the purchase orders are not signed and returned to the contracting office within 5 business days of receipt, a Phase I award will not be issued. 

PHASE I: This topic is intented for technology that has proven it can go directly into a Phase II SBIR, and thus will not have a Phase I. 

PHASE II: Develop, install, integrate and demonstrate the proposed solution prototype system. This demonstration should focus specifically on: 1. Evaluating the proposed solution against the proposed objectives and measurable key results. 2. Describing in detail how the installed solution differs from the non-defense commercial offering to solve the Air Force need and how it can be scaled to be adopted widely (i.e. how can it be modified for scale) 3. A clear transition path for the proposed solution that takes into account input from all affected stakeholders including but not limited to: end users, engineering, sustainment, contracting, finance, legal, and cyber security. 4. Specific details about how the solution can integrate with other current and potential future solutions. 5. How the solution can be sustainable (i.e. supportability) 6. Clearly identify other specific DoD or governmental customers who want to use the solution 

PHASE III: This is the main goal of this topic, we intend for many of the solutions to go straight from Phase II to Phase III as soon as the product-market fit has been verified. The contractor will transition the adapted non-defense commercial solution to provide expanded mission capability to a broad range of potential government and civilian users and alternate mission applications. 

REFERENCES: 

1. FitzGerald, B., Sander, A., & Parziale, J. (2016). Future Foundry: A New Strategic Approach to Military-Technical Advantage. Retrieved June 12, 2018, from https://www.cnas.org/publications/reports/future-foundry; 2. Blank, S. (2016). The Mission Model Canvas – An Adapted Business Model Canvas for Mission-Driven Organizations. Retrieved June 12, 2018, from https://steveblank.com/2016/02/23/the-mission-model-canvas-an-adapted-business-model-canvas-for-mission-driven; 3. US Department of Defense. (2018). 2018 National Defense Strategy of the United States Summary, 11. Retrieved from https://www.defense.gov/Portals/1/Documents/pubs/2018-National-Defense-Strategy-Summary.pdf

KEYWORDS: Open, Other, Disruptive, Radical, Dual-Use, Commercial 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop and demonstrate a low cost aerial platform capable of transporting 2-4 military personnel (one in medical litter) with no onboard traditional pilot and capable of at least 100 mile radius at speeds above 100kts and taking off and landing at unprepared locations approximately 50 by 50 feet but no larger than 150 ft. for supporting combat search and rescue, personnel recovery, and special operations in the field. 

DESCRIPTION: In supporting the 2018 National Defense Strategy there is a need to deploy, survive, operate, maneuver, and regenerate in all domains while under attack in theaters throughout the globe. Along with operations in the Middle East, new capabilities must also support operations in the Indo-Pacific and Africa regions. This Global Operating Model will expose the US military to operations across the world in diverse environments. These diverse environments will require operations from new isolated locations, at greater distances, requiring low cost solutions for increasing our options for providing transport of small teams of personnel into and out of harm's way without increasing the number of personnel at risk (the aircrew) needed to move these teams. There have been significant advancements in Short Take-Off and Landing (STOL) aircraft as well as traditional rotorcraft design that may provide solutions to the challenge. In addition, the significant private sector investment that could be leveraged for this military mission is the personal air vehicle (PAV) and urban air mobility (UAM) efforts. These efforts have been focused on urban operations for on-demand civilian transport and have many parallel design requirements to that desired under this SBIR but with some modifications to meet the military mission. The PAV market and infrastructure needed for full access to the US National Airspace System (NAS) is a barrier for many US based companies to compete in this sector. Collaboration between the military and US companies supporting the PAV market means the potential for early adoption of PAV technology by the military for this mission area while preserving the US industrial base. While the number of designs and potential solutions for the PAV and UAM market increase, their designs are not optimized for a military solution. Many of the PAV designs have been self-limiting to an electric only solution or speed, weight, or range limited to fit into certain design categories as defined by the FAA for ease of fielding. For the purpose of this effort these limitations are not applicable and the main focus is on military utility. By providing lower cost options compared to traditional manned assets and ease of operations through autonomy, the vision is to increase the number of recovery/transport vehicles available across the battlefield and to decrease the response time needed for insertion and extraction of personnel at risk while also not increasing the number of personnel in harms way. The personnel recovery / transport vehicle envisioned is highly autonomous and flown either remotely through secure datalink similar to unmanned aircraft systems/remotely piloted aircraft in use by Air Force and Department of Defense (DoD), or through minimal control inputs by the person onboard and not requiring significant training. The transport can carry a minimum of two personnel with one person potentially in a litter and needs to be accessible by the other person while in flight. Optimally the platform can carry up to four military personnel with full equipment load totaling approximately 1400 pounds. The aircraft must be capable of performing the full mission with 1400 pounds of personnel and cargo at 4000 ft./95°F or higher at speeds above 100kts. The minimal combat radius of 100 nautical miles (200 miles range) with a minimum of 30 minutes of reserves for emergency or divert. The platform has the capability of operating in all theaters of operation to include desert, jungle, mountainous, and maritime (ship to shore transport). Water recovery of personnel is a desired capability but not a requirement. The platform’s signatures should be minimalized to reduce detection where able with focus on lowest acoustic audible signature when taking off and landing with a landing zone that is not presurveyed and measuring approximately 50 by 50 feet but no larger than 150 ft. Unlike the civil PAV concepts to be quiet throughout flight and requiring all electric designs, a hybrid propulsion system with increased acoustic signatures while enroute is acceptable to gain speed and range desired for the military mission. The air vehicle should be transportable by military aircraft (preferably by C-130 or H-47) and would optimally be capable of being airdropped for staging or mission execution. Vehicles capable of being transported via a CV-22 are of interest but not required. The vehicle should be fully contained (not requiring special equipment, launch, and recovery systems) and capable of ground handling and assembly and launch by aircrew in 30 minutes. The final solution will likely be composed of a system of systems that can be tailored to application and budget. 

PHASE I: Proposal must show, as appropriate to the proposed effort, technical feasibility of the underlying technology, understanding and experience in the air vehicle market, understanding and experience in air vehicle development, experience to construction, testing, and delivery of production quality air vehicles. FEASIBILITY DOCUMENTATION: Offerors interested in submitting a Direct to Phase II proposal in response to this topic must provide documentation to substantiate that the scientific and technical merit and feasibility described has been met and describes the potential commercial applications. The documentation provided must substantiate that the proposer has developed a preliminary understanding of the technology to be applied in their Phase II proposal to meet the objectives of this topic. Documentation should include all relevant information including, but not limited to: technical reports, test data, prototype designs/models, and performance goals/results. Read and follow all of the feasibility documentation portions of the Air Force 19.2 Instructions. The Air Force will not evaluate the offeror’s related D2P2 proposal where it determines that the offeror has failed to demonstrate the scientific and technical merit and feasibility of the Phase I project. 

PHASE II: Develop and demonstrate an air vehicle platform capable of being transportable by military aircraft (preferably by C-130 or H-47), assembled in 30 minutes by ground crews, and carrying up to four military personnel with full equipment load totaling approximately 1400 pounds at 4000 ft./95°F or higher at speeds above 100kts with a minimal combat radius of 100 nautical miles (200 miles range) and 30 minutes of reserves for emergency or divert. For the Phase II effort, the aircraft may be tested manned or unmanned but must be capable of being operated onboard by a non-rated operator (no pilot training). During the Phase II effort, air drop operations will not be required. 

PHASE III: The contractor will pursue commercialization of the various technologies developed in Phase II for potential government applications. There are potential commercial applications in a wide range of diverse fields that include cargo transport operations centers, industrial systems monitoring, and security response command centers. 

REFERENCES: 

1. Lascara, B., Spencer, T., DeGarmo, M., Lacher, A., Maroney, D., & Guterres, M. (2018) Urban Air Mobility Landscape Report. The MITRE Corporation. Retrieved from https://www.mitre.org/sites/default/files/publications/pr-18-0154-4-urban-air-mobility-landscape-report_0.pdf; 2. Mouton, Christopher A., Jia Xu, Endy M. Daehner, Hirokazu Miyake, C. R. Anderegg, Julia Pollak, David T. Orletsky, and Jerry M. Sollinger,. (2015) Rescuing Downed Aircrews: The Value of Time. Santa Monica, CA: RAND Corporation. Retrieved from https://www.rand.org/pubs/research_reports/RR1106.html. Also available in print form.; 3. Mouton, Christopher A. and John P. Godges, (2016) Timelines for Reaching Injured Personnel in Africa. Santa Monica, CA: RAND Corporation. Retrieved from https://www.rand.org/pubs/research_reports/RR1536.html. Also available in print form.; 4. National Academies of Sciences, Engineering, and Medicine. 2018. Combat Search and Rescue in Highly Contested Environments: Proceedings of a Workshop–in Brief. Washington, DC: The National Academies Press. https://doi.org/10.17226/25156.

KEYWORDS: Unmanned Aircraft, Mobility, Personal Air Vehicle, STOL, VTOL, Rescue, Transport, Automation, Urban Air Mobility 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop and demonstrate a high altitude, inexpensive, rapidly disposable, quiet (audible detection of under 150ft), precision air delivery system for small packages (<25lbs in a volume of up to 1.4ft3) that is capable of being deployed from either a door (required method) or ramp (optional method) of a host aircraft to enable rapid resupply of troops supporting combat search and rescue, personnel recovery and special operations in the field at a standoff distance of up to 100 miles. The payloads may contain sensitive electronics such as handheld radios or delicate medical supplies and should be delivered undamaged to a 10ft x 10ft target zone. The system should be able to be deployed from the side door of an aircraft at the operating limits of a C-17 (45,000 ft. and 515 mph). 

DESCRIPTION: Users desire a capability to quickly deliver critical supplies to troops in remote and austere locations as well as combat search and rescue and personnel recovery. Current air delivery methods are tailored for large packages (palletized loads), and in contrast, this topic seeks an inexpensive method for precision delivery of smaller packages (<25lbs in a volume of up to 1.4 ft3) from a variety of airborne platforms from (preferably) the side door at the operating limits of a C-17 (45,000 ft. and 515 mph). The system should be capable of delivering the payload to a 10ft x 10ft target zone using soft landing techniques to protect sensitive and delicate payloads. The inexpensive, expendable delivery system should not require aircraft integration and is capable of launching from a variety of military and civilian aircraft both fixed and rotary wing. The system should not require additional tools to install or remove payload items. The system should support rapid destruction and disposal on the ground by the payload recipient (<5 minutes of all airframe components and electronics that could be repurposed or reverse engineered). The system should not require propulsion, but powered options may be explored later in the program to extend the stand-off distance. Additionally, the topic requires delivery of small packages, but higher payloads may be explored later in the program. The system should consist of an air vehicle, deployment device (if required), autopilot, ground control station/programming device, and associated systems to allow safe separation and deployment from a host aircraft from up to 45,000ft and 515mph. The autopilot should provide the ability to set or change the coordinates by loadmasters onboard the aircraft prior to the deployment. The system will not be controlled or updated once launched and does not require anti-jam capabilities. The preferred method is a tube launched style aircraft but the topic is open to new revolutionary ideas. 

PHASE I: Proposal must show, as appropriate to the proposed effort, technical feasibility of the underlying technology, understanding and experience with aerial delivery systems, understanding and experience in air vehicle payload development and integration, experience to construction, testing, and delivery of production quality air delivery systems. FEASIBILITY DOCUMENTATION: Offerors interested in submitting a Direct to Phase II proposal in response to this topic must provide documentation to substantiate that the scientific and technical merit and feasibility described has been met and describes the potential commercial applications. The documentation provided must substantiate that the proposer has developed a preliminary understanding of the technology to be applied in their Phase II proposal to meet the objectives of this topic. Documentation should include all relevant information including, but not limited to: technical reports, test data, prototype designs/models, and performance goals/results. Read and follow all of the feasibility documentation portions of the Air Force 19.2 Instructions. The Air Force will not evaluate the offeror’s related D2P2 proposal where it determines that the offeror has failed to demonstrate the scientific and technical merit and feasibility of the Phase I project. 

PHASE II: Develop and demonstrate a prototype air delivery system that can deliver small packages (<25lbs in a volume of up to 1.4 ft3) that is capable of being deployed from either a door (required method) or ramp (optional method) of a range of aircraft to enable rapid resupply of troops supporting combat search and rescue, personnel recovery and special operations in the field at a standoff distance of 100 miles. Demonstrate that payloads containing sensitive electronics such as handheld radios or delicate medical supplies and can be delivered undamaged to a 10ft x 10ft target zone. Demonstrate the ability to be safely deployed from the side door of a host aircraft at the operating limits of a C-17 (45,000 ft. and 515 mph). Demonstrate rapid destruction and disposal on the ground by the payload recipient (<5 minutes of all airframe components and electronics that could be repurposed or reverse engineered) of the aircraft. Choose the test aircraft, which can be manned or unmanned, to be representative of the target application. Develop test and safety documentation and support processes for test and safety approvals required for this demonstration. Develop models to evaluate the device/system cost in low rate production. 

PHASE III: The contractor will pursue commercialization of the technologies developed in Phase II for potential government and commercial applications. Government applications include delivery of supplies to personnel for disaster recovery and emergency response. There are potential commercial applications in a wide range of diverse fields that include commercial package delivery, medical supply delivery, and recreation. 

REFERENCES: 

1. David Boura, Keith Strang, William Semke, Richard Schultz, and Danny Hajicek. "Automated Air Drop System for Search and Rescue Applications Utilizing Unmanned Aircraft Systems", Infotech@Aerospace 2011, Infotech@Aerospace Conferences; 2. Milgram, J. et al, "Autonomous Glider Systems for Logistics Delivery", Presented at the AUVSI 2003 Unmanned Systems Symposium and Exposition, Baltimore, MD, July 15–17, 2003 http://citeseerx.ist.psu.edu/viewdoc/download?doi=10.1.1.510.3079&rep=rep1&type=pdf; 3. Rosen, J. (2019). Blood from the sky: an ambitious medical drone delivery system hits Rwanda. [online] MIT Technology Review. Available at: https://www.technologyreview.com/s/608034/blood-from-the-sky-ziplines-ambitious-medical-drone-delivery-in-africa/ [Accessed 15 Jan. 2019].; 4. Xu, Jia, Design Perspectives on Delivery Drones. Santa Monica, CA: RAND Corporation, 2017. https://www.rand.org/pubs/research_reports/RR1718z2.html.

KEYWORDS: Precision, Aerial, Delivery, Low Cost, Small Payload, Cargo, High Altitude, Resupply 

TECHNOLOGY AREA(S): Air Platform 

OBJECTIVE: Develop system level concepts for transformational air mobility operations, particularly airlift / cargo delivery, and develop designs for enabling elements of these concepts. 

DESCRIPTION: Air Mobility Command's (AMC) mission is to provide rapid, global mobility and sustainment for America's armed forces. AMC provides airlift, aerial delivery and aerial refueling, and also plays a crucial role in providing humanitarian support at home and around the world. The fleet of C-17, C-5, and C-130 aircraft provide the bulk of the airlift / cargo delivery capability for AMC. These aircraft provide a range of capabilities that span much of the airlift needs. However, there is considerable opportunity to transform the ways and means for performing air mobility operations, and simultaneously address emerging new missions and threats, and increase capacity while reducing costs. AMC’s “Rapid Global Mobility Vision 2016-2035” provides a call to “find new and innovative means and methods to acquire new, and modernize existing, air mobility force structure and systems in a timely and cost-effective manner.” 

PHASE I: Proposal must demonstrate, as appropriate to the proposed effort, understanding and experience in the military or commercial airlift / cargo delivery market, a system level concept for modernization or transformation of the military air delivery enterprise, technical feasibility of the underlying elements and technology of this concept, understanding and experience in air vehicle development, experience to construction, testing, and delivery of production quality air vehicles. FEASIBILITY DOCUMENTATION: Offerors interested in submitting a Direct to Phase II proposal in response to this topic must provide documentation to substantiate that the scientific and technical merit and feasibility described has been met and describes the potential commercial applications. The documentation provided must substantiate that the proposer has developed a preliminary understanding of the technology to be applied in their Phase II proposal to meet the objectives of this topic. Documentation should include all relevant information including, but not limited to: technical reports, test data, prototype designs/models, and performance goals/results. Read and follow all of the feasibility documentation portions of the Air Force 19.2 Instructions. The Air Force will not evaluate the offeror’s related D2P2 proposal where it determines that the offeror has failed to demonstrate the scientific and technical merit and feasibility of an equivalent Phase I project. 

PHASE II: Refine system concepts for enhancing / transforming the military airlift / cargo delivery enterprise, to include air vehicles, cargo handling, and ground operations. Develop comprehensive conceptual or preliminary designs for the elements of this concept. Perform high fidelity system analyses to quantify capability, performance and cost and compare to existing operations. Identify and develop, as appropriate, enabling technologies, component, or designs for this revolutionary concept. 

PHASE III: The contractor will pursue commercialization of the various technologies developed in Phase II for potential commercial and government applications. There are potential commercial applications in cargo transport. 

REFERENCES: 

1. Rapid Global Mobility Vision. May 2016, Retrieved from http://www.airforcemag.com/DocumentFile/Documents/2016/Rapid%20Global%20Mobility%20Vision.pdf; 2. Owens, R.C., Theater Airlift Modernization: Options for Closing the Gap, Joint Force Quarterly 75, 30 September 2014, Retrieved from https://ndupress.ndu.edu/JFQ/Joint-Force-Quarterly-75/Article/577555/theater-airlift-modernization-options-for-closing-the-gap/.; 3. Owens, R.C., Shaping Air Mobility Forces for Future Relevance, Air University, Air Force Research Institute Paper 2017-1, January 2017, Retrieved from https://media.defense.gov/2017/Jun/19/2001765023/-1/-1/0/AP_2017-1_OWEN_AIR_MOBILITY_FORCES.PDF

KEYWORDS: Unmanned Aircraft, Mobility, Personal Air Vehicle, STOL, VTOL, Rescue, Transport, Automation 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Advance the ability of SOCOM Operators and mission commands to incorporate existing physics-based analysis tools into mission planning methods to enable the rapid prediction of weapons effects on user-defined targets and hazards to non-targets. 

DESCRIPTION: Recent advances in physics-based analysis have demonstrated that accurate simulation results of complex weapon/target interactions are achievable within viable timeframes. Existing fast running tools have historically been used to aid mission planning; although these tools can provide quick answers, the results lack the fidelity, accuracy, and flexibility offered by the physics-based models. Incorporation of the physics-based simulations into a faster platform, and then pairing this with a more accessible user visualization interface would result in a planning tool that offers accurate and detailed results of the new simulations at the speeds and convenience of existing fast running tools. Current capabilities could be expanded and enhanced, or supplemented, to better address SOCOM’s current and future needs. The result would be a custom graphical user interface (GUI) that includes simple user input; quick, accurate, and detailed results; the ability to load, save, share, and compare scenario results; and cross-platform functionality to address end-user needs. Mission information, in the form of scenario input parameters, should be entered interactively and intuitively into the planning tool through the customized GUI. This input process may be accomplished in one or more ways, including 1) selection from libraries of predefined weapons, targets, and other details to build the scenarios of interest, 2) loading previously analyzed scenarios and modifying these to fit the current situation, and 3) creating custom engagement scenarios by modifying weapons or targets within the library or by directly creating new weapons and targets. The user should have flexibility to easily explore various weapons and targets, including but not limited to: structural geometry, impact angle, detonation scheme, aim point, and weapon and target composition. The intuitive GUI should facilitate easy scenario generation and encourage “what-if” scenario exploration. The predicted results of each scenario will be conveyed in a simple and accessible format that spans the needs of users of varying experience and technical expertise. The GUI will allow users to easily access the top-level results for a quick understanding of the outcome of any scenario, but also allow a format to intuitively step down into more detail on each parameter of interest, when needed. The planning tools should also enable users to easily compare multiple engagement scenarios at various levels of detail, and then to save and share customized targets, scenarios, and results. The planning tool will also use high-fidelity simulation to better quantify the extent and severity of collateral hazards. The proposed planning tool must be configured to work on platforms relevant to SOCOM, including both laptop PCs and tablets. All features within the software must be accessible across PC and tablet operating environments. In addition the contractor must implement the Munitions End Game visualization tool using AFRL’s Endgame Framework architecture which is used to develop weapon effects simulations across the DoD. The Endgame Framework is a vulnerability/lethality modeling and simulation architecture that provides the capability to support and integrate traditionally separate airborne, surface mobile, ground fixed, and directed energy threat analyses, by providing many core functions including a 3D geometry engine, interactive GUI and a simulation executive controller. To this end, Endgame Framework will be provided along with the necessary documentation. 

PHASE I: Submitting for Direct to Phase II. 

PHASE II: Leveraging advances from multiple highfidelity computational physics based effects analysis programs, develop, install, and demonstrate a prototype planning tool system as describe above. 

PHASE III: This system could be used in other military applications where SOF and general purpose forces can use detailed effects analysis to plan operations. This capability could also be adopted by other organizations such as Homeland Security and federal law enforcement to protect critical assets. 

REFERENCES: 

1. Mann, J., Fisher, D., Kraus., Lowndes, E., and York, A. “An Analysis of Engagement Algorithms for Real-Time Weapons Effects.” JDMS, vol. 3, no. 3, 2006, pp.189-201. Semantics Scholar, https://pdfs.semanticscholar.org/6f86/0d75a585d72ab19d181864ae8b0f9eef1062.pdf; 2. A. Kurtz, J. Cogar, S. Treadway, X. Xiao, “Advanced Lagrangian Techniques for Modeling Missile Defense Intercepts.” 2009 AIAA Weapons System Effectiveness Conference, August 2009, Tucson, AZ.; 3. Driels, Morris. Weaponeering: Conventional Weapon System Effectiveness. American Institute of Aeronautics and Astronautics, 2013.

KEYWORDS: Weapon Effects, Physics-based, Analysis, Database, Mission Planning, Engagement Scenarios, GUI 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a laser projection system capable of projecting paint and masking schemes over the entirety of a large frame aircraft. 

DESCRIPTION: The 402nd AMXG at Robins AFB have identified the repainting and masking procedures of large frame aircraft to be a crucial bottleneck in the administration of depot level maintenance. Currently, masking, paint, and decal locations are determined through the very time consuming process of meticulously measuring several locations by hand to lay out the proper scheme in accordance with T.O. 1C-130A-23 in conjunction with T.O. 1-1-8. An opportunity exists to project entire paint and masking schemes over the body of these large aircraft, removing the need to reiterate measurements for every aircraft, while eliminating human error and drastically decreasing repaint times. DIRECT TO PHASE II: USAF AFSC/EN will only accept Direct to Phase II proposals. 

PHASE I: FEASABILITY DOCUMENTATION: for this Direct to Phase II topic, USAF AFSC/EN is expecting that the submittal firm substantiate a present ability to: - Determine the technical feasibility of developing a 3-D paint projection system to be utilized for the masking and painting of large frame aircraft, to include, but not limited, to C-130. - Demonstrate ability of current hardware and software in “3-D Paint Projection Processes”1 of aircraft utilizing “Systems and Methods for Optically Projecting Three-Dimensional Text, Images and/or Symbols onto Three-Dimensional Objects”2 in which paint schemes, symbols, assembly instructions, etc. can be projected onto full, 3-D aircraft bodies with high precision and no distortion of the image. 

PHASE II: Develop, demonstrate, and deliver a system capable of translating projection technologies directly onto large frame aircraft, to include, but not limited, to C-130. The Phase II deliverable should optimize a “3-D Paint and Masking Projection System” to overcome the technology gaps established by the size of large frame aircraft, the lack of technical data (CAD models) associated with the aircraft, and the variation of feature locations on these aircraft due to natural wear and tear. 

PHASE III: Refine and mature the system to be marketed to other defense and commercial customers who require the ability to quickly project and apply masking and paint schemes onto large frame aircraft. 

REFERENCES: 

1. “Gulfstream Launches 3-D Paint Projection Process”, Gulfstream News, https://www.gulfstreamnews.com/news/gulfstream-launches-3-d-paint-projection-process, 30 June 2016.; 2. “Systems and methods for optically projecting three-dimensional text, images and/or symbols onto three-dimensional objects”, Google Patents, https://patents.google.com/patent/US4575330A/en, 09 Nov 2009.; 3. “Laser Products and Instruments,” https://www.fda.gov/Radiation-EmittingProducts/RadiationEmittingProductsandProcedures/HomeBusinessandEntertainment/LaserProductsandInstruments/default.htm

KEYWORDS: Projection, Masking, Painting 

TECHNOLOGY AREA(S): Chem Bio_defense 

OBJECTIVE: Develop a decontamination kit and procedure for decontamination of field-exposed military working dogs. 

DESCRIPTION: Military Working Dogs (MWDs) are at risk from exposure to a range of hazardous chemicals encountered during military operations. These include the classical chemical warfare agents (CWAs) including mustard (HD), nerve agent (VX) and G-agents, as well as Toxic Industrial Chemicals (TICs), and abused drugs such as opioids. On such exposure, it is essential to have an effective decontamination system to eliminate the hazard as rapidly as possible to protect both the dogs and their handlers. The objective of this topic is to create a military working dog decontamination kit that can achieve a contamination level objective of 90% reduction in starting challenge (2 LD50s based on average weight of a canine (80-100 lbs)) until thorough decontamination can be conducted. The military working dog decontamination kit will be lightweight, highly portable and designed for use in the field within one hour of contamination by a single handler in Personal Protective Equipment (PPE; includes protective mask, suit, gloves and boots) with limited external resources. Potential military working dog decontamination kit materials could include but are not limited to an indicator or detector of contamination, and existing decontamination technologies such as Reactive Skin Decontamination Lotion (RSDL), sorbents, wipes, and reactive chemical solutions. Veterinary dermatological (or other) treatments with potential efficacious properties for chemical agents could also be considered. The procedures and decontamination technologies should take into account features of working dogs and potential decontamination areas with different physical characteristics, including fur, skin, paws, eyes, nose and ears, and liquid agent wicking from hair to skin follicles. Offerors should keep in mind the size and type of breeds typically utilized in military operations including Belgian Malinois, German Shepherd and Labrador Retriever. If tests with live animals are proposed, that work must be conducted in accordance with all applicable animal use regulations. The military working dog decontamination kit should be modular to allow the warfighter to select critical components as needed. The kit could be split and partially carried on the canine in small pouches on sides of a vest; however these must be light and soft materials (tearable pouches, rollable to fit into packs, etc.). 

PHASE I: Determine potential indicator or detector technologies that can be used to ascertain contamination on the canine, and determine decontamination candidates to include wet and dry decontaminants for chemical agents for use in the field with limited external resources. Decontamination candidates should not require additional water or consumables and should be easily utilized when the handler is in full PPE. Evaluate the effectiveness of the highest priority identified decontamination materials, methods and toxicity on fur, paws, eyes and skin using a chemical surrogate on canine cadavers. Threats include simulants for mustard and nerve agents. Verify that total remaining simulant can be reduced to or below performance objective levels. Down-select the best decontamination candidate(s) for inclusion in the military working dog decontamination kit for development and testing in Phase II. Analyze and document the potential effects of the decontamination materials and processes on handlers. Estimate costs, transportability and storage stability of the materials. 

PHASE II: Demonstrate the decontamination effectiveness against live mustard and nerve agents such as HD, GD, and VX on biopsy, excised skin or canine cadavers. Validate that the total remaining agent is at or below performance objectives. Chemical agent testing must be conducted at an approved DoD facility, or commercial facility that has been approved to handle DoD generated agents. Demonstrate modularity of kit components. Deliver ten (10) military working dog decontamination kits, each containing decontamination supplies sufficient to decontaminate one (1) contaminated military working dog, a clean leash/collar system and muzzle for the MWD post-decon, and instructions for most efficacious decontamination of military working dogs with these materials. In addition, each kit should be clearly labeled for K9 use. 

PHASE III: PHASE III: Optimize the decontamination kit and process with additional threats, and demonstrate its effectiveness with end users in a field test, e.g., potentially a chemical/biological operational assessment or advanced technology demonstration. Use feedback from end-users to further optimize the decontamination kit. PHASE III DUAL USE APPLICATIONS: This technology will be valuable to military working dogs, police dogs, and other similar working dogs involved at various government agencies, as well as dog handlers/trainers. 

REFERENCES: 

1: Acute Exposure Guideline Levels for Airborne Chemicals, U.S. Environmental Protection Agency, https://www.epa.gov/aegl.

2:  Handbook of Chemical and Biological Warfare Agent Decontamination by G.O. Bizzigotti, R.P. Rhoads and S.J. Lee

3:  ILM Publications, 2012.

4:  Health Effects of Project Shad Chemical Agent: VX Nerve Agent. 2004 Prepared for the National Academies by The Center for Research Information, Inc.

5:  Field Management of Chemical and Biological Casualties Handbook 5th Ed. 2016, Borden Institute US Army Medical Department Center and School Health Readiness Center of Excellence, US Army Medical Research Institute of Chemical Defense, Office of the Surgeon General US Army, pp. 149-174.

KEYWORDS: Canine, Military Working Dog, Decontamination, Chemical Warfare, Hazardous Materials 

TECHNOLOGY AREA(S): Chem Bio_defense, Materials 

OBJECTIVE: Develop a self-contained decontamination system for on-site treatment of contaminated personal gear and equipment. 

DESCRIPTION: In recent years, the number of terrorist incidents involving chemical weapon agents continues to rise. There is high potential that the warfighter may encounter similar and emerging threats on the battlefield. To limit the spread of contamination and restore combat operations, there is an essential need for a self-contained, field decontamination system for on-site treatment of both personal and sensitive equipment. The system will decontaminate a broad spectrum of chemical and biological (CB) agents from a variety of equipment within 8-hours while not compromising the integrity or function of the equipment, allowing it to be returned to normal operations without limitations. Performance objectives are a 10,000 fold (4-log) decrease of a chemical agent starting at a 1 gram per square meter loading and 1,000,000 fold decrease (6-log) of viable biological agents starting at a 107 loading of colony forming units (CFU). Examples of gear include but are not limited to helmets, tactical vests, and sensitive equipment such as radios and night-vision goggles. For the purposes of this topic, sensitive equipment will be modeled on a military-style, multi-channeled, hand-held radio that the vendor will use (and acquire) to verify and validate performance of the decontamination system. A potential approach would be to place the contaminated equipment in a portable enclosure that maintains the effective decontamination conditions for the necessary duration. The self-contained system would require only equipment that could be readily transported. Assume that additional electrical power will not be available on-site and that JP8 will be the only fuel available. 

PHASE I: Develop a decontamination platform/process based on technologies or combinations of technologies that have proven effectiveness (TRL 4) against a broad range of CB agents on relevant military materials. Construct a “breadboard” prototype and demonstrate that the device achieves the necessary conditions at all points of the targeted sensitive item that will be decontaminated. Demonstrate neutralization of contamination on a sensitive equipment mock-up. Demonstrate decontamination of this item using a chemical surrogate that simulates the relevant properties of HD or VX, and a qualified biological surrogate targeted to simulate the relevant properties of bacillus anthracis spores. Establish the time and conditions required, and verify that total remaining agent (simulant) can be reduced to performance objective levels. Show through analysis that conditions in the decontamination process will not harm the equipment being decontaminated. Estimate the logistic requirements of the proposed process. 

PHASE II: Refine the design and construct a “brassboard” prototype that provides the form, fit and function of the targeted end product. Demonstrate the decontamination effectiveness against HD, GD and VX chemical agents, and a qualified bacillus anthracis spore surrogate on the model sensitive item. Validate that total remaining agent is at or below performance objectives. Demonstrate and validate that the conditions of the process do not have a deleterious impact on the immediate or long-term function of the modeled sensitive item. The prototype will include management of effluents to ensure agents or harmful chemicals are contained during the process. Chemical agent testing must be conducted at an approved DoD facility, or commercial facility that has been approved to handle DoD generated agents. 

PHASE III: PHASE III: Refine the prototype design. Demonstrate that it can decontaminate a broader range of sensitive equipment. Provide military users prototypes for field-testing. Obtain user feedback to further refine the design. PHASE III DUAL USE APPLICATIONS: This technology will be valuable to both military personnel and first responders for on-site decontamination. 

REFERENCES: 

1: Handbook of Chemical and Biological Warfare Agent Decontamination by G.O. Bizzigotti, R.P. Rhoads and S.J. Lee

2:  ILM Publications, 2012.

3:  Myers, J. (2018) "Chemical Hot Air Decontamination of Sulfur Mustard Contaminated Personal Effects." EPA Decontamination Research and Development Conference.

4:  Buhr et al. J. Appl. Microbiol. 119, 1263-1277.

5:  Lalain, T.

6:  Mantooth, B.

7:  Shue, M.

8:  Pusey, S.

9:  Wylie, D. The Chemical Contaminant and Decontaminant Test Methodology Source Document, Second Edition

10:  ECBC-TR-980

11:  U.S. Army Edgewood Chemical Biological Center: Aberdeen Proving Ground, MD, 2012. UNCLASSIFIED Report. DTIC Access Number ADA566601.

KEYWORDS: Decontamination, Personal Protective Equipment, Chemical Warfare Agent, Biological Warfare Agent, Hazardous Materials 

TECHNOLOGY AREA(S): , Chem Bio_defense 

OBJECTIVE: Develop or adapt a mass spectrometer based instrument with two-dimensional analytical capability with a “smart” inlet valve – the valve will open and admit a pre-separated analytical sample from atmospheric pressure, or near atmospheric pressure, only when the sample is presented to the mass spectrometer inlet. Pre-separated samples may be ionic species from an Ion Mobility Spectrometer (IMS) or neutral effluent from a Gas Chromatograph (GC). 

DESCRIPTION: Mass Spectrometry (MS) has been identified as a fundamental technology for analysis of molecular signatures to detect the presence of and identify chemical threat species in aerosol and vapor form. Mass spectrometers (also MS) operate under vacuum conditions and as a result, significant electrical power is expended to produce the vacuum. If a MS inlet can be controlled to open for a short time at precisely the time a pre-separated sample is present at the inlet, power consumption can be reduced. For example, if the inlet valve is open 10% of the time, only 10% of the MS gas load experienced with a continuously sampling inlet will have to be pumped. Development of a MS inlet synchronized to pre-separated neutral samples or pre-separated ionic species presupposes that the separation system is at or near atmospheric pressure. The sample separation system and the MS may be orthogonal technologies, e.g., gas chromatography and mass spectrometry (GC-MS) or complementary technologies, e.g., ion mobility spectrometry and mass spectrometry (IMS-MS). In a GC-MS instrument, neutral samples at or near atmospheric pressure are periodically introduced into the MS inlet with ionization occurring at a reduced pressure inside the MS. IMS-MS requires an ionization source external to the MS and ion (or sample separation) occurs at or near atmospheric pressure. The synchronized MS inlet would be keyed to a GC retention time of a sample of interest or to an ion species drift time in an ion mobility spectrometer. The key aspect of the solicited innovation is the synchronized MS sample inlet. Development includes mechanical design, electronic operation and software/firmware control of the synchronized inlet to minimize the MS vacuum requirements and reduce power consumption. Reducing vacuum requirements will prolong detector operation while utilizing battery power, smaller vacuum pumps can be used, and the vacuum envelope will be reduced in size. As advances in network architectures and decision logic mature, there is increasingly a need to quantify the concentration of a suspected threat plume in order to address the likelihood of a true positive detection event and to characterize the nature and extent of contamination or hazard presented by the incident. Recent developments have resulted small mass-based methods, i.e., ion mobility spectrometry and mass spectrometry, however, improvements in minimizing size, weight and power consumption can still be realized. 

PHASE I: The feasibility/proof-of-concept study will use a GC-MS or IMS-MS instrument operating on laboratory power with the synchronized MS inlet valve. Emphasis is placed on design, construction and operation of a synchronized MS inlet. Assessment of power consumption is paramount. The instrument may consist of commercial-off-the-shelf or specialized components in as small a form factor as possible with a projection of size, weight, power, sensitivity, and analytical resolving power of an instrument to be prototyped in Phase II. Vacuum pump size and power consumption will be minimized. Operational software will be developed to demonstrate the utility of the synchronized inlet. Key performance metrics associated with the technical approach will include low power consumption and will also include detection and identification of airborne chemical threats to include Chemical Warfare Agent (CWA) simulant (surrogate) compounds. Analytical system surrogate to surrogate compounds are directly indicative of responses to CWA. CWA responses would be accomplished in Phase II. 

PHASE II: The Phase II effort will fabricate, integrate, test, and optimize performance of a synchronized MS inlet as a part of a real-time two-dimensional vapor analysis platform based on the outcome of the Phase I analysis of the MS inlet and 2-dimensional instrument feasibility study. Offerors should perform quantitative assessment tests of the prototype platform using CWA simulant compounds. Chemical surrogates include high volatility, semi-volatile and low volatility compounds. Affordability, response time, and size, weight and power (SWaP) are critical evaluation criteria for the candidate technology. To be competitive and suitable for military threat monitoring, the technology must not cost more than $10,000 per system in production of 100s of units per year; must respond in 60 seconds or less, and not exceed SWaP constraints of one (1) kilogram (kg) including batteries, less than 650 cubic centimeters (cm3), and 24-hour operation using commercial off-the-shelf batteries. Offerors will make Phase II prototype instrumentation available to the appropriate DoD laboratory/facility to confirm quantitative assessment tests with actual chemical warfare agents to include, at a minimum, nerve and blister agents. Note, the Phase II prototype instrumentation cannot be returned to the Offeror. 

PHASE III: PHASE III: During Phase III, a real time, quantitative, multicomponent analytical capability will be finalized to enable the development of novel air-monitoring technologies suitable for defense and security applications and for industrial and commercial environments. The instrumentation will exist in portable form, powered by on-board commercial-off-the-shelf battery power. The instrument will have capability for sampling airborne analytes, vapors and aerosols. The capability to quantitatively define the concentration of gas phase constituents in real time would lead to new products for process and environmental quality monitoring in the pharmaceutical, semiconductor, and advanced materials industries. Additionally, the quantitative vapor/aerosol monitoring technology developed in conjunction with this SBIR topic would enable a wide variety of application models, to include compliance, safety and health, medicinal/diagnostic monitoring, and industrial/medical process monitoring. Offerors should enunciate a definitive commercialization strategy for gas monitoring and quantification technology including a market analysis for the DoD applications and other health and safety, environmental surveillance, diagnostic and industrial monitoring applications. PHASE III DUAL USE APPLICATIONS: The real time, quantitative, multicomponent enables development of novel air-monitoring technology suitable for applications in defense and national security, law enforcement (drug interdiction, drugged driving), and First Responder safety as well as applications for compliance, health and safety, environmental surveillance, diagnostic and industrial monitoring applications. 

REFERENCES: 

1: "A compact high performance ion mobility – linear ion trap mass spectrometer for high accuracy explosives and drug detection," Ching Wu, et al., 10th Annual Trace Explosives Detection Workshop, Ottawa, Ontario, Canada

2:  April 2018.

3:  "Miniature and Fieldable Mass Spectrometers: Recent Advances," Dalton T. Snyder, et al.

4:  Anal. Chem., 2016, 88 (1), pp 2–29.

KEYWORDS: Mass Spectrometry, Inlet Valve, Sample Introduction, GC/MS, Vapor Analysis 

TECHNOLOGY AREA(S): Chem Bio_defensebio Medical 

OBJECTIVE: Development of effective phage therapy as a medical countermeasures to treat bio-threat specific bacteria: Burkholderia mallei, Burkholderia pseudomallei, or Brucella spp. 

DESCRIPTION: The Department of Defense (DoD) has a requirement to field medical countermeasures to treat diseases resulting from intentional or environmental exposure to CBRN agents. The DoD threat agent list includes the bacteria B. anthracis, Y. pestis, F. tularensis, B. mallei, B. pseudomallei, and Brucella spp. Drug resistance to antibiotics has emerged as a major obstacle for multiple bacteria including DoD threat organisms (1). Additionally, more effective therapeutics and alternate therapies are urgently needed to cure infections caused by bio-threat bacteria including antibiotic resistant strains. The practice of phage therapy to treat bacterial infections has been conducted for almost a century (2, 3). Increased rate of antibiotic resistance in bacteria has generated interest in phage therapy. Biotechnological advances in this area allow the generation of bioengineered phages and purified phage lytic proteins (4). Suitable phage delivery systems may be required to ensure their prolonged survival, better phage retention at target site and reduction in their rapid clearance by mononuclear phagocytic system (MPS). Several nano-delivery systems composed of an assortment of different sizes, shapes, and materials have been constructed (5-9). Current research on the use of phages and their lytic proteins, specifically against multi-drug resistant bacterial infections suggests phage therapy has the potential to be used as either an alternative or a supplement to antibiotic treatment (3). The primary goal of this SBIR topic is to identify and characterize phages as an alternative to antibiotics for the treatment of diseases caused by Category B bio-threat bacteria: B. mallei, B. pseudomallei, or Brucella spp (4, 10-12).  

PHASE I: Development of phage libraries/cocktails. Key objectives of this Phase are: 1. Preparation of phage libraries/cocktails for treatment of: B. mallei, B. pseudomallei, or Brucella spp. 2. Optimize and expand phage libraries to provide therapeutic coverage of multiple, diverse strains: B. mallei, B. pseudomallei, or Brucella spp using in vitro and in situ methodologies. 3. Analyze and provide potency testing data of phages. Select phage or phage library/cocktails for in vivo testing. 

PHASE II: Determination of efficacy and toxicity data in relevant animal models. Key objectives of this Phase are: 1. Demonstrate in vivo activities of phages or phage libraries in appropriate animal models. 2. Evaluation of dose, efficacy and toxicity of phages in appropriate animal models. 3. Analyze and submit in vivo screening data. 4. As needed, Formulate, Test, and Develop enhanced delivery systems (e.g. liposomes, exosomes, phospholipid vesicles) to improve efficacy of phage candidate therapeutic cocktails in in vivo models of infection. 5. Provide a plan for Good Manufacturing Practice (GMP) manufacture of product phage or phage library/cocktails, product licensure /approval to support the Warfighter (prototypes). This plan should also support product application under an Emergency Use Authorization (EUA) or an Emergency Investigational New Drug (eIND).  

PHASE III: PHASE III: Conduct non-clinical and clinical testing of phages necessary to achieve EUA or eIND status for treatment of B. mallei, B. pseudomallei, or Brucella spp as an alternative to or in combination with current antimicrobial therapeutics 

REFERENCES: 

1: USAMRIID Medical Management of Biological Casualties Handbook. September 2014, 8th Edition.

2:  Lin DM, Koskella B, Lin HC (2017) Phage Therapy: An alternative to antibiotics in the age of multi-drug resistance. World J. Gastrointest. Pharmacol. Ther.8:162-173.

3:  Chanishvili N. (2012) Phage Therapy- history from Twort and d’Herelle through Soviet experience to current approaches. Adv. Virus Res. 83:3-40.

4:  Umaporn Yordpratum, Unchalee Tattawasart, Surasakdi Wongratanacheewin, Rasana W. Sermswan (2011) Novel lytic bacteriophages from soil that lyse Burkholderia pseudomallei, FEMS Microbiology Letters.314:81–88.

5:  S. Singla, K. Harjai, K. Raza, S. Wadhwa, O.P. Katare, S. Chhibber (2016) Phospholipid vesicles encapsulated bacteriophage: A novel approach to enhance phage biodistribution, J. of Virological Methods.236:68-76.

6:  Singla S, Harjai K, Katare OP, Chhibber S (2016) Encapsulation of Bacteriophage in Liposome Accentuates Its Entry in to Macrophage and Shields It from Neutralizing Antibodies. PloS ONE 11(4): e0153777. doi:10.1371joumal.pone.0153777.

7:  Zhigang Ju & Wei Sun (2017) Drug delivery vectors based on filamentous bacteriophages and phage-mimetic nanoparticles, Drug Delivery, 24:1898-1908.

8:  Chhibber S, Kaur J, Kaur S (2018) Liposome Entrapment of Bacteriophages Improves Wound Healing in a Diabetic Mouse MRSA Infection. Frontiers in Microbiology. 9:561.

9:  Malik DJ, Sokolov IJ, Vinner JK, Mancuso F, Cinquerrui S, Vladisavljevic GT, Clokie MRJ, Garton NJ,Stapley AGF, Kipichnikova A (2017). Formulation, stabilization and encapsulation of bacteriophage for phage therapy. Adv. Colloid Interface Sci. 249:100-133.

10:  https://www.cdc.gov/phpr/publications/2008/appendix6.pdf

11:  Fillippov AA, Sergueev KV, and Nikolich MP (2013) Bacteriophages against Biothreat Bacteria: Diagnostic, Environmental and Therapeutic Applications. J. of Bioterrorism and Biodefense. S3:010.doi:10.4172/2157-2526.S3-010.

12:  Guang-Han 0, Leang-Chung C, Vellasamy KM, Mariappan V, Li-Yen C, Vadivelu J (2016) Experimental Phage Therapy for Burkholderia pseudomallei Infection. PLoS ONE 11 (7): e0158213. doi:10.1371joumal.pone.0158213.

KEYWORDS: Bacteriophage, Phage, Biothreat, Medical Countermeasure, Biotherapeutic, Drug Screening 

TECHNOLOGY AREA(S): Chem Bio_defensebio Medical 

OBJECTIVE: Innovate a portable/handheld non-invasive device to measure intracranial pressure (ICP) to support development of medical countermeasures. 

DESCRIPTION: As stated in the President’s National Biodefense Strategy for 2018, “a collaborative, multi-sectoral, and trans-disciplinary approach” is necessary for a robust biodefense enterprise. Therefore, development of advanced diagnostics and/or triage capabilities for infected individuals ideally should occur concomitantly with the development of medical countermeasures (MCMs). This topic seeks to develop a novel device for non-invasive monitoring of intracranial pressure (ICP). ICP measurement has been used for diagnosis of traumatic brain injury (TBI), and a similar need exists for measuring ICP changes resulting from infections of the Central Nervous System (CNS), particularly in laboratory animals such as non-human primates (NHP). Ultimately, a device of this nature will be desired to measure ICP in humans. The preferred device must rapidly and reproducibly identify increases in ICP in infected non-human primates; it would also be desirable if the data derived from this method be compatible with data obtained through the use of standard telemetry systems. 

PHASE I: Innovate a novel non-invasive device to measure intracranial pressure in a non-human primate. Demonstrate function using existing animal or human data or via a simulation of intracranial pressure without use of non-human primates. 

PHASE II: Further develop and test the portable (handheld), non-invasive ICP device in a non-human primate infected with an infectious disease. The infection should include CNS involvement and must induce an increased ICP. Infectious diseases of interest include but are not limited to: alphaviruses, West Nile virus, tick-borne encephalitis virus (TBEV), henipaviruses, etc., or bacterial agents that cause meningitis/encephalitis such as Neisseria meningitides, Streptococcal species, etc. 

PHASE III: PHASE III: Further development and refinement of the device developed in Phase II, for use in Food and Drug Administration (FDA) supervised Animal Rule studies conducted under Good Laboratory Practice (GLP). PHASE DUAL USE APPLICATIONS: A portable non-invasive device for measuring ICP has multiple uses in the civilian health care sector for treatment of patients with traumatic brain injury and encephalitis caused by bacterial or viral infection. 

REFERENCES: 

1: National Biodefense Strategy 2018. https://www.whitehouse.gov/wp-content/uploads/2018/09/National-Biodefense-Strategy.pdf

2:  Kawoos U, McCarron R, Auker C, and Chavko M. Advances in Intracranial Pressure Monitoring and Its Significance in Managing Traumatic Brain Injury. International Journal of Molecular Sciecne, Vol 16, Issue 12, 2015.

3:  Freeman W. Management of Intracranial Pressure. Continuum Lifelong Learning in Neurology, Neurocritical Care Vol 21, Issue 5, 2015.

KEYWORDS: Intracranial Pressure, Encephalitis, Diagnostic Medical Device 

TECHNOLOGY AREA(S): Chem Bio_defensebio Medical 

OBJECTIVE: Develop and demonstrate efficacy of broadly active antiviral drug(s) to be used as a therapeutics in the event of disease or as prophylactic medical countermeasures (MCM) following human exposure or threat of exposure to emerging viral agents. 

DESCRIPTION: Emerging Viruses posing a threat to the warfighter include members from the following virus groups: Alphaviruses – (e.g. Venezuelan equine encephalitis virus [VEEV]; Eastern equine encephalitis virus [EEEV], and Western equine encephalitis virus [WEEV]) Filoviruses – (e.g. Zaire ebolavirus [EBOV]; Sudan ebolavirus [SUDV]; Bundibugyo ebolavirus [BDBV]; Marburg virus [MARV]) Bunyaviruses - (e.g. Hantaan virus [HTNV]; Rift Valley Fever virus [RVFV]; Severe Fever with Thrombocytopenia Syndrome virus [SFTSV]; Crimean-Congo Hemorrhagic Fever virus [CCHFV]; Sin Nombre virus [SNV]). Arenaviruses – (e.g. Lassa virus [LASV]; Lujo [LUJV]; Guanarito [GTOV]; Junín [JUNV]; Machupo [MACV]; Sabia [SABV]; & Chapare viruses) Paramyxoviruses – (e.g. Nipah [NiV] & Hendra [HeV] viruses) Coronaviruses – (e.g. Severe acute respiratory syndrome-related coronavirus [SARS-CoV]; Middle East respiratory syndrome-related coronavirus [MERS-CoV]; & Porcine deltacoronavirus [PDCoV]) The mucosal route of challenge (via aerosol route of exposure) from weaponized pathogens presents a distinct threat to force health protection. Indeed, the health of deployed warfighters can be threatened by the previously listed viruses used as bioweapons, as well as by natural routes of infection, nosocomial, or human-to-human transmission via the mucosal route with these same viruses. With targeted deployment of troops to specific regions, the probability of the “risk” of certain diseases from natural exposure and subsequent person-to-person spread increases, as well as the consequences for overall unit and mission readiness following an outbreak1,2. A recent example is the deployment of U.S. troops to assist in the 2014-2016 EBOV epidemic in West Africa1,2. An unmitigated bioweapons attack would pose an additional risk with potential for severe consequences to both unit health and military strength and capabilities. The five groups of viruses discussed below can be transmitted to humans by natural route (sometimes through insect vectors) and by intentional release as weaponized pathogens; once in the human population, several can spread via direct human-to-human transmission adding secondary and tertiary cases from the initial exposure event. The common theme across these unrelated viruses is pathogenesis resulting from mucosal route of exposure. The three members of the Alphavirus genus cause encephalitic disease in both horses and humans. Natural infection is acquired by mosquito bite; however, all three viruses are highly infectious by aerosol exposure. This characteristic along with stability, ease of passage, and receptiveness to genetic manipulation make these viruses excellent candidates for bioweapons. Indeed, the post-WWII biological warfare programs of several countries (including the U.S.) incorporated production of alphaviruses as potential bioweapons3. In contrast to disease from natural infection, which is sporadic and primarily results in a self-limiting febrile illness with rare transition to encephalitis, disease from aerosol exposure from even a low dose ( <102 pfu, plaque forming units) results in symptomatic disease in humans and nonhuman primates (NHPs)4. Furthermore, disease from a bioweapons attack likely would involve a higher challenge dose. Disease from VEEV regardless of route of exposure is typically nonlethal and manifests as a febrile illness in young adult to middle-aged humans and NHPs, and is strain, dose, and age dependent. Infections typically resolve within the second week without sequelae, and severe encephalitis is rare, although encephalitis in children carries a higher mortality rate. Sequelae are rare from VEEV infection; however, at least with NHPs, clearance of the virus from the CNS is prolonged and abnormalities by EEG can be detected long after disease resolution (unpublished). Warfighter return to duty is theoretically possible following resolution (in the second week of illness), but questions remain regarding virus clearance from the brain and the possibility of residual neurological manifestations (e.g. circadian rhythm disturbances). Use of VEEV as a potential bioweapon is further enhanced by the very short incubation period to as little as 24hrs with a mean time of 2.7 days4. Disease resulting from natural route or aerosol exposure from WEEV to EEEV range from intermediate to severe relative to VEEV but also are dose, strain, and age dependent. Encephalitic disease is more severe and typically lethal in EEEV infections in both humans and NHPs3,5. For human patients who do resolve WEEV and EEEV encephalitis, sequelae are significant and common5 and warfighter return to duty in survivors would be doubtful. Filoviruses are among the four virus families causing viral hemorrhagic fevers –mild to severe vascular dysregulation as a result of virus infection from members of Flaviviridae, Filoviridae, Arenaviridae and Bunyaviridae6, 7. The Filoviridae family includes ebolaviruses (EBOV) and Marburg virus (MARV) and are responsible for severe hemorrhagic fever outbreaks with high case fatalities in Africa. While most have occurred in Central Africa, the largest and most complex of the 20+ filovirus outbreaks occurred in West Africa from 2014-2016. The second largest outbreak of EBOV is ongoing in eastern Democratic Republic of the Congo (DRC) with nearly 1000 infected patients to date and over 500 fatalities9,10. As with other viral hemorrhagic fever viruses, EBOV and MARV are zoonotic viruses that also can be transmitted human-to-human via multiple routes of infection from the index case11. These are highly infectious viruses at low dose, are stable on surfaces for extended periods of time, and can be transmitted by the aerosol route. The aerosol route of transmission also was demonstrated in nonhuman primate studies8. Given these criteria, including multiple routes of human-to-human transmission, and the real possibility that the virus could become endemic in humans in parts of Africa, the WHO lists filovirus disease on its list of top emerging diseases likely to cause major epidemics or pandemics12. Therefore, the viruses presents both potential public health and bioweapons threats. Arenaviruses are one of the four different groups of viruses causing viral hemorrhagic fever (VHF) worldwide. Arenaviruses are rodent-associated, zoonotic, RNA viruses divided into Old World and New World classifications based on several criteria including geographical differences. Infection typically occurs via mucosal exposure to rodent urine or contact with contaminated rodent material (e.g. bedding) and human-to-human transmission. Many of the arenaviruses (e.g. Junin virus) cause significant morbidity and mortality at relatively low doses and are stable and highly infectious via aerosol route making these viruses suitable for weaponization6,13. Old World arenaviruses causing VHF include Lassa virus (LASV) and the recently identified Lujo (LUJV) virus. Lassa virus is endemic in West Africa, and some areas of Central Africa. Most infections are mild or asymptomatic with severe VHF in approximately 20% of cases; this translates to approximately 300,000-500,000 cases per year in West Africa with approximately 5000 deaths, although reporting is incomplete. Among hospitalized patients, the case fatality rate approaches 70%14,15. LUJV is an emerging Arenavirus first isolated in 2008 from a cluster of five patients in South Africa with the original index case from Zambia. Other outbreaks have not been detected; however, the virus infection was fatal in four of the five cases, and the incident suggests that zoonotic transmission of arenaviruses is a cause for concern throughout Africa16. New World arenaviruses causing VHF include Guanarito (GTOV), Junín (JUNV), Machupo (MACV), Sabia (SABV), and Chapare viruses and are regionally associated throughout South America6,13,28. As with the Old World viruses, these arenaviruses are associated with rodents and are transmitted through mucosal exposure to aerosols or introduced via abraded skin by contact with infected rodent carcasses and tissues, and by close human-to-human contact with an infected patient. Outbreaks resulting from members of the Bunyavirales order (formerly referred to as Bunyaviruses) have occurred as recently as 2018 in global areas of U.S. military presence. These viruses are arboviruses and/or associated with rodent species similar to Arenaviruses. The presence of vectors in new areas where these viruses are not currently endemic could lead to expansion of endemic areas or pose sporadic outbreak risks. For example, SFTSV is a new emerging Phlebovirus in China, Japan, and South Korea that causes hemorrhagic fever with mortality rates of up to 30%, and the tick vector for SFTSV was isolated recently in the U.S., specifically in states with military installations used for training larger numbers of personnel17. Furthermore, autochthonous infection (non-imported) has been demonstrated for CCHFV, a Nairovirus whose global distribution in over 30 countries is second to Dengue virus. Members of the Hantaviridae family of Bunyaviruses are characterized as Old or New World hantaviruses and cause hemorrhagic fevers with either renal syndrome (HFRS) or a hantavirus pulmonary (or cardiopulmonary) syndrome (HPS & HCPS)18. These viruses are associated with rodents, and primary infection generally occurs after contact with aerosolized, rodent excreta. Rarely, human-to-human and nosocomial transmissions have been documented19. Zoonotic Coronaviruses (e.g. SARS-CoV, MERS-CoV, PDCoV) also pose a threat to the warfighter in global areas. Within the past 15 years, three zoonotic and potentially zoonotic Coronaviruses have been identified as the viral agents causing severe acute respiratory illnesses with significant morbidity and mortality. SARS-CoV was identified in 2003 as causing atypical pneumonia with a mortality rate of 11%; MERS-CoV was identified in 2012 and since that time has caused over 2066 cases, mostly in Saudi Arabia, with a mortality rate of 36%20-23 and refs therein. In 2012, another coronavirus (porcine deltacoronavirus, PDCoV) was identified as a globally distributed enteropathogen in swine24. PDCV contains genetic lineages from avian and mammalian coronaviruses suggesting an ability for cross-species transmission. Emerging zoonotic paramyxoviruses (Nipah, NiV & Hendra, HeV viruses) within the genus Henipavirus have caused almost yearly outbreaks with high mortality rates within the last twenty years and are among the top 8 prioritized, emerging infectious diseases identified by the WHO because of a broad mammalian host range, multiple strains of individual viruses, and the ability to transmit human-to-human following the index case25-27. Outbreaks have occurred in Asia - mainly in Malaysia, Singapore, eastern India, and Bangladesh, and a similar virus causing a Nipah-like infection in the Philippines was recently identified26. Of concern is the spread of the viruses to new areas, such as the 2018 Nipah virus outbreak in Kerala state on the Arabian Sea side of the southern tip of India in May 201829. While both Nipah and Hendra viruses can be transmitted human-to-human, these cases to date have remained largely within close contacts and caregivers; however, the possibility of mutation leading to broader human-to-human transmission, the use of multiple hosts (in contrast to other more host-restrictive paramyxoviruses), as well as multiple routes of transmission is a continuing epidemiological concern. Given the highly infectious capability of the Paramyxoviridae family, mutation leading to greater transmission or weaponization of these emerging viruses would pose a significant threat to public and warfighter health. Currently, there are no FDA approved therapies or vaccines to treat or prevent infections by the emerging viruses discussed in the preceding paragraphs. A number of vaccines and therapeutics (including small molecules, monoclonal antibodies, and antibody cocktails) are in the Investigational New Drug (IND) stage of development, but none are approved for use in humans to date. Difficulties encountered with many of these experimental products have included: a lengthy requirement to attain a therapeutic dose, safety signals in clinical trials, viral mutation leading to resistance, inability to neutralize different viruses within the same family, or limited protection over time. Therefore, continued efforts to identify medical countermeasures will be needed to develop multi-generational products to effectively prevent or manage disease from these viral threats. 

PHASE I: Identify broadly acting small molecule inhibitors of virus infection. Phase I proof-of-concept/feasibility studies will be accomplished by: A) Identification and development of working stocks of appropriate strains of virus(es) for testing. Alternatively, surrogate assays (e.g. pseudotyped particles, replicase assays) in lower safety containment laboratories are sufficient for early screening. B) Using high throughput screening of existing or novel libraries, identify inhibitors to virus replication of one or more of the members of the virus families previously discussed. Modeling data for broad-spectrum inhibition of replication can be used to begin intermediate development at the Phase II Period of Performance. The screening should assess in vitro antiviral activity and cytotoxicity. 

PHASE II: Optimize the lead compound identified in Phase I through medicinal chemistry approaches to enhance in vitro antiviral activity. Further assessment of antiviral activity will be provided through preclinical efficacy studies. This stage will require development of working stocks of appropriate strains of virus(es) for testing if not developed in Phase I and performance within high containment laboratories. 

PHASE III: PHASE III: Preclinical development of down-selected candidates to support submission of an application for an IND. Construction of a Development Plan through consultation with a sponsor and the U.S. Food and Drug Administration (FDA). Discussions and preparations would include identification of appropriate virus strains, animal models, additional animal model studies, development of Good Manufacturing Practices (GMPs) and the conduct of safety trials. PHASE III DUAL USE APPLICATIONS: The viral agents listed in this SBIR topic lack treatment options, and any therapeutic derived from this research will be of significant use for both civilian and military populations at risk. 

REFERENCES: 

1: Murray CK, Yun H, Markelz AE, Okulicz JF, Vento TJ, Burgess TH, Cardile AP, Miller RS. 2015. Operation United Assistance: Infectious Disease threats to Deployed Military Personnel. Military Medicine 180:626-651.

2:  O’Donnell FL, Stahlman S, Fan M. 2018. Surveillance for vector-borne diseases among active and reserve component service members, U.S. Armed forces, 2010-2016. MSMR 25:8-16.

3:  Steele, K.E., Reed, Douglas R, & Glass, P. 2007. Alphavirus encephalitides. Medical Aspects of Biological Warfare. 241-270.

4:  Rusnak JM, Dupuy LC, Niemuth NA, Glenn AM, Ward LA. 2018. Comparison of Aerosol- and Percutaneous-acquired Venezuelan Equine Encephalitis in human and nonhuman primates for suitability in predicting clinical efficacy under the Animal Rule. Comp. Med. 68:1-16.

5:  Steele, K.E. & N. Twenhafel. 2010. Pathology of animal models of alphavirus encephalitis. Veterinary pathology. 47. 790-805. 10.1177/0300985810372508.

6:  Paessler S. and Walker, D.H. 2013. Pathogenesis of Viral Hemorrhagic Fevers. Annu. Rev. Pathol. Mech. Dis. 8:411-40.

7:  http://www.cidrap.umn.edu/infectious-disease-topics/vhf

8:  Baseler L, Chertow DS, Johnson KM, Feldmann H, Morens DM. 2017. The Pathogenesis of Ebola Virus Disease. Annu. Rev. Pathol. Mech. Dis. 12:387-418.

9:  http://www.cidrap.umn.edu/news-perspective/2019/02/ebola-still-claiming-lives-drc-cases-climb-835

10:  https://www.who.int/ebola/situation-reports/drc-2018/en/

11:  https://www.who.int/news-room/fact-sheets/detail/ebola-virus-disease

12:  http://www.who.int/emergencies/diseases/2018prioritization-report.pdf?ua=1

13:  Golden JW, Hammerbeck CD, Mucker EM, Brocato RL. 2015. Animal Models for the Study of Rodent-Borne Hemorrhagic fever virus: Arenaviruses and Hantaviruses. Biomed Res. Intl. Vol 2015.

14:  Azeez-Akande O. 2016. A Review of Lassa Fever, An Emerging Old World Hemorrhagic Viral Disease in Sub-Saharan Africa. African J. Clin & Exp Microb. 17:282-289.

15:  Hallam HJ, Hallam S, Rodriguez SE, Barrett ADT, Beasley DWC, Chua A, Ksiazek TG, Milligan GN, Sathiyamoorthy V, Reece LM. 2018. Baseline mapping of Lassa fever virology, epidemiology and vaccine research and development. NPJ Vaccines 3:11.

16:  Briese T, Paweske JT, McMullan LK, Hutchison SK, Steet C, Palacios G, Khristova ML, Weyer J, Swanepoel R, Egholm M, Nichol ST, Lipkin WI. 2009. Genetic Detection and Characterization of Lujo Virus, a New Hemorrhagic Fever-Associated Arenavirus from Southern Africa. PLoS Pathog. 5:e1000455.

17:  Liu S, Chai C, Wang C, Amer S, LV H, He H, Sun J, Lin J. 2014 Systematic Review of Severe Fever With Thrombocytopenia Syndrome: Virology, Epidemiology, and Clinical Characteristics. Rev. Med. Virol.24:90-102.

18:  DC Pignott and Dembek ZF. 2017. CBRNE- Viral Hemorrhagic Fevers. https://emedicine.medscape.com/article/830594

19:  Martinez-Valdebenito C, Calvo M, Vial C, Mansilla R, Marco C, Palma RE, Vial PA, Valdivieso F, Mertz G, Ferres M. 2014. Person-to-Person Household and Nosocomial Transmission of Andes Hantavirus, Southern Chile, 2011. Emerging Inf Dis 20:1629-1636.

20:  Bailey ES, Fieldhouse JK, Choi JY and Gray GC. (2018) A Mini Review of the Zoonotic Threat Potential of Influenza Viruses, Coronaviruses, Adenoviruses, and Enteroviruses. Front. Public Health 6:104.

21:  Yin Y and Wunderink RG. (2018) MERS, SARS, and other coronaviruses as causes of pneumonia. Respirology 23:130-137.

22:  Van Doremalen N and Munster VJ. (2015) Animal Models of Middle East Respiratory Syndrome Coronavirus Infection. Antiviral Res. 122:28-38.

23:  WHO. Coronavirus infections. (2015) http://www.who.int/emergencies/mers-cov/en/

24:  Li W, Hulswit RJG, Kenney SP, Widjaja I, Jung K, Alhamo MA, van Dieren B, van Kuppeveld FJM, Saif LJ, Bosch BJ. (2018) Broad receptor engagement of an emerging global coronavirus may potentiate its diverse cross-species transmissibility. PNAS 115:E5135-E5143.

25:  Clayton BA. (2017) Nipah virus: transmission of a zoonotic paramyxovirus. Current Opinion in virology 22:97-104.

26:  Thibault, et al., (2017) Zoonotic potential of merging paramyxoviruses: knowns and unknowns. Adv. Virus res. 98:1-55.

27:  http://www.who.int/emergencies/diseases/2018prioritization-report.pdf?ua=1

28:  Charrel RN, de Lamballerie X, Emonet S, 2008. Phylogeny of the genus Arenavirus. Curr Opin Microb 11:362-368.

29:  https://www.who.int/csr/don/07-august-2018-nipah-virus-india/en/

KEYWORDS: Antiviral, Small Molecule, High Throughput, Bunyavirus, Arenavirus, Viral Hemorrhagic Fever, Alphavirus, Ebolavirus, Filovirus, Paramyxovirus, Coronavirus 

TECHNOLOGY AREA(S): Chem Bio_defensebio Medical 

OBJECTIVE: Develop optimized protein/glycoengineered platform technologies to produce gram quantities of purified, biologically active rBChE protein that can be utilized as an effective medical countermeasure against organophosphorus (OP) Chemical Warfare Agent (CWA) exposure. The optimized rBChE, in a fully glycosylated, sialylated, tetrameric form analogous to the human plasma wild-type configuration, could be utilized as a broad spectrum, prophylactic or therapeutic treatment after intravenous delivery. 

DESCRIPTION: Butyrylcholinesterase (BChE) is a naturally occurring human-derived plasma protein that is efficacious as a prophylactic and as a post-exposure, pre-symptomatic treatment against OP CWA exposure. BChE acts as a stoichiometric bioscavenger that binds to and inactivates OP CWA in the bloodstream, thereby preventing the CWA from reaching critical target organs. Optimally active BChE is a tetrameric (mediated by a proline–rich attachment domain or PRAD protein) enzyme that requires glycosylation and sialylation for prolonged circulatory half-life in vivo (1-4). Purification of sufficient quantities of active, natural BChE from blood plasma is inefficient, low yield, and expensive. Multiple alternative recombinant, molecular biology approaches (e.g., PER.C6, CHO, transgenic goat milk, Nicotiania, and Baculovirus) have produced active rBChE; however, the recombinant proteins have had limited efficacy and short in vivo circulating half-lives. These shortcomings have primarily been due to inappropriate configuration of glycans, lack of proper sialylation, and production of short half-life, monomeric and dimeric forms. Long circulating, active rBChE can now be optimally and efficiently produced by novel cellular and molecular platforms that employ modern, targeted protein and glycoengineering technologies. Specifically, cellular platforms can be engineered to over express optimized proline-rich chaperones, specific branching glycosyltransferases, in combination with α 2,6 sialyltransferases to produce correctly configured BChE. These novel protein/glycoengineering technologies can thus be utilized to produce gram quantities of glycosylated and sialylated, tetrameric rBChE for non-clinical testing and evaluation as a precursor to clinical development. 

PHASE I: Genetically-engineer DNA constructs that express secreted, active monomers/dimers of enzymatically active rBChE in selected cellular platform. Develop a tetramerization strategy via genetically engineered proline-rich attachment domain (PRAD)-like protein peptide or polyproline peptides. Alternatively, evaluate tetramerization employing external extracellular addition of PRAD like peptides or polyproline (2-4). The objective is to produce tetrameric rBChE with enzymatic activity. 

PHASE II: Employ a specific protein/glycoengineering strategy to optimize the correct expression of proline-rich chaperones, mannose N-glycan, and α-2,6 linked sialylation (N-acetylneuraminic acid). The optimized configuration would duplicate the configuration of human wild-type plasma rBChE (correctly glycosylated, sialylated, tetramer) (5). Approaches might include overexpression of sialyltransferases and other glycosyltransferases, manipulation of sialic acid biosynthetic pathways and inhibition of sialidases, or glycosylation site insertion and manipulation of glycan heterogeneity to produce the desired glycoforms (6-8). The platform objective yield is grams of product. Demonstrate optimized enzymatic (> 621 U/mg) and functional binding activity in vitro of the optimized tetrameric rBChE (with CWA or surrogates). 

PHASE III: PHASE III: Evaluate pharmacokinetic and pharmacodynamic blood plasma profile in guinea pigs and/or other appropriate species administered properly glycosylated, tetrameric BChE. Compare to published studies or reports of human-derived BChE administered intravenously to various species, including human. Develop scale-up process for pilot-lot production of tetrameric rBChE. Develop a current Good Manufacturing Practices (cGMP) manufacturing strategy. PHASE III DUAL USE APPLICATIONS: Successful development of the optimized protein/glycoengineering platform technologies can be readily adapted to other recombinant proteins of clinical interest to both the military and civilian communities. These could include vaccines and other therapeutic recombinant proteins. 

REFERENCES: 

1: Involvement of oligomerization, N-glycosylation and sialylation in the clearance of cholinesterases from circulation. Kronman C, Velan B, Marcus D, Ordetlich A, Reuveny S, Shafferman, A. Biochem J. (1995) 311, 959-967.

2:  Polyproline promotes tetramerization of recombinant human butyrylcholinesterase. Larson M, Lockridge O, Hinrichs S. Biochem. J. (2014) 462, 329-335.

3:  Lamellipodin proline rich peptides associated with native plasma butyrylcholinesterase tetramers. Li H, Schopfer L, Masson P, Lockridge O. Biochem J. (2008) 411, 425-432.

4:  Proline-Rich Chaperones Are Compared Computationally and Experimentally for Their Abilities to Facilitate Recombinant Butyrylcholinesterase Tetramerization in CHO Cells. Wang Q, Chen CH, Chung CY, Priola J, Chu JH, Tang J, Ulmschneider MB, Betenbaugh MJ. Biotechnol J. 2018 Mar

5:  13(3):e1700479. Epub 2017 Nov 17

6:  Glycoproteomics characterization of butyrylcholinesterase from human plasma. Kolarich D, Weber A, Pabst M, Stadlmann J, Teschner, W, Ehrlich H, Schwarz H, Altmann, F. Proteomics 2008, 8, 254-263.

7:  Glycoengineering of CHO Cells to Improve Product Quality. Wang Q, Yin B, Chung CY, Betenbaugh MJ. Methods Mol Biol. 2017

8: 1603:25-44.

9:  Strategies for Engineering Protein N-Glycosylation Pathways in Mammalian Cells. Wang Q, Stuczynski M, Gao Y, Betenbaugh MJ. Methods Mol Biol. 2015

10: 1321:287-305.

11:  A novel sugar analog enhances sialic acid production and biotherapeutic sialylation in CHO cells. Yin B, Wang Q, Chung CY, Bhattacharya R, Ren X, Tang J, Yarema KJ, Betenbaugh MJ. Biotechnol Bioeng. 2017 Aug

12: 114(8):1899-1902.

KEYWORDS: Butyrylcholinesterase, Bioscavenger, Nerve Agent Poisoning, Chemical Countermeasure, Glycosylation, Sialylation, Recombinant Human Butyrylcholinesterase, RBChE 

TECHNOLOGY AREA(S): Chem Bio_defensebio Medical 

OBJECTIVE: To develop a stable, intermuscular (IM) formulated drug product for a long duration opioid antagonist, or novel opioid medical countermeasures (MCM) (e.g., respiratory stimulants, non-µ-opioid receptor MCMs) to provide both immediate relief from opioid poisoning, as well as prolonged protection from re-intoxication. The drug product is intended for use by U. S. Department of Defense (DoD) Service Members in far-forward deployed settings and must be an effective and suitable long duration rescue therapy for opioid casualties. 

DESCRIPTION: The DoD seeks to develop and field medical countermeasures to treat the toxic symptoms following opioid poisoning. The high availability of synthetic opioids, such as fentanyl and its derivatives, is a threat to both the civilian and military communities [1-4]. The rapid onset of respiratory depression creates a critical need to quickly administer adequate doses of MCM to immediately reverse adverse effects. Furthermore, it would be advantageous to field an MCM with a sustained efficacy profile to either: 1) provide protection against opioid toxicity greater than 8 hours; 2) allow time for evacuation of a casualty to definitive care, usually within 1 to 2 hours without the chance of renarcotization; or 3) eliminate the need for evacuation [5-9]. Commercially available naloxone products, 2 mg EVZIO® autoinjector and 4 mg Narcan® (naloxone) nasal spray, are effective for immediate rescue from respiratory depression. However, naloxone’s half-life that is shorter than the duration of action of many opioids, including carfentanil. This results in the need for additional doses of naloxone due to renarcotization [1, 6, 7, 9]. Naloxone’s short half-life makes it desirable to develop and field a MCM in an autoinjector with either a longer duration of action or one that uses a mechanism other than µ-opioid receptor antagonism to counteract opioid poisoning. Currently, long acting opioid antagonists are available; however, there are none available in cGMP formulations suitable for IM injection. The DoD is also interested in novel opioid MCMs such as respiratory stimulants (e.g., ampakines) and non-µ opioid receptor MCMs that would allow for use of current opioid pain management protocols. The rapid delivery of long acting opioid antagonists or other novel opioid MCMs is paramount for soldiers to remain ambulatory to complete the mission or move though a clean/dirty line for transition to a higher echelon of medical care. An opioid casualty encountered during DoD and Joint Forces missions will differ from casualties encountered by civilian emergency response teams. Civilian first responders primarily treat opioid overdoses in diverse populations with co-morbidities. They are concerned with precipitating withdrawal symptoms following naloxone treatment. Conversely, in the DoD and the Joint Services, the MCM will be administered to non-opioid dependent, healthy individuals with few or no underlying medical conditions. As such, safe administration of high doses of opioid antagonists with low regret may be readily performed in military settings. On a battlefield, the capability for IM delivery of an immediately acting opioid antagonist followed by a longer acting MCM could be lifesaving and mission essential. The goal is to eventually deliver these treatments via an autoinjector device. This topic seeks to develop a rescue therapeutic for IM administration that provides a longer duration or improved capability over naloxone products. The MCM could be a novel opioid antagonist, target a non-µ opioid receptor, or work by a novel mechanism. IM administration is the preferred route of administration. The medical countermeasures are intended to be delivered as self- and buddy-aid, as well as at higher roles of care (i.e., hospital). The drug product should be stable and suitable for use across a wide range of temperatures in operationally relevant environmental conditions. The drug product should be administered by trained personnel with little effort and low operational and logistical burden. The drug product will require Food and Drug Administration (FDA) approval/licensure, as will the combination drug-device delivery system. This award mechanism will bridge the gap between laboratory-scale innovation and entry into a recognized FDA regulatory pathway leading to commercialization and eventual combination with an autoinjector. 

PHASE I: Establish preliminary specifications of the opioid medical countermeasure for both immediate effect and extended release/longer duration formulations or drug. Predict human MCM dosages for IM administration that would result in efficacious blood levels within 3 – 5 minutes and sustained levels for a minimum of 8-hours. The desired final volume is to be no more than 2.0 mL. In vitro binding studies with multiple opioid receptor subtypes and other preliminary in vitro study design(s) for efficacy are desired. No animal use is permitted during this proof-of-concept/feasibility phase. 

PHASE II: Evaluate the candidate drug product for performance and conduct of early animal trials. Evaluation should include detailed characterization of performance of IM injection in a suitable animal model, demonstrate in vivo efficacy against opioid poisoning, and conduct toxicology and safety studies required to support an IND, 510(k), or related FDA filing. Conduct early formulation stability assessments for chemical degradation and at operationally relevant temperature conditions. The objective is to achieve at least two-year stability at room temperature. Initiate pharmacokinetic (PK) studies of the optimized formulation prototype or drug in relevant animal models. The objective is to determine the plasma levels of the drug after a single IM injection and determine the Cmax and the AUCtotal, Tmax and the elimination half-life (EC50). Considerations for how the drug product will be manufactured consistent with FDA guidelines and amenable to industry best practices (e.g., cGMP and ISO13485:2016) should be documented. 

PHASE III: PHASE III: The small business firm with an appropriate partner will complete non-clinical and IND enabling studies initiated in Phase II and conduct human Phase 1 clinical trials to establish human safety and obtain pharmacokinetic performance data. PHASE III DUAL USE APPLICATIONS: A full spectrum opioid MCM formulation could be utilized by medical professionals, law enforcement agents, and first responders to reduce toxicity and mortality of opioid poisoning. For example, law enforcement agents or first responders, a population which presumably is also non-opioid dependent, could use the medical countermeasure upon accidental exposure to opioids. 

REFERENCES: 

1: World Health Organization, Expert Committee on Drug Dependence 39th Meeting. Carfentanil: Critical Review Report. Agenda item 4.8. 6-10 November 2017.

2:  NDEWS. Special Report: Fentanyl and fentanyl analog: National drug early warning system (NDEWS)

3:  2015 [updated December 7 2015].

4:  Kinetz E, Satter R. Ohio is hardest hit by Chinese carfentanil trade, logging 343 of more than 400 seizures in US. Associated Press. November 3, 2016. http:// http://www.ohio.com/news/local/ohio-is-hardest-hit-by-chinese-carfentanil-trade-logging-343-of-more-than-400-seizures-in-u-s-1.724486. Accessed February 10, 2017.

5:  Sutter ME, Gerona RR, Davis MT, Roche BM, Colby DK, Chenoweth JA, Adams AJ, Owen KP, Ford JB, Black HB, Albertson TE. Fata fentanyl: One pill can kill. Academic Emergency Medicine. 2017

6:  24(1) 106-113.

7:  Drug Enforcement Agency (DEA). Fentanyl. A briefing guide for first responders. 2017. Available from: https://www.dea.gov/druginfo/Fentanyl_BriefingGuideforFirstResponders_June2017.pdf

8:  Faul M, Lurie P, Kinsman JM, Dailey MW, Carbaugh C, Sasser SM. Multiple naloxone administrations among emergency medical service providers is increasing. Prehospital Emergency Care. 2017

9:  21(4): 411-419.

10:  Somerville MJ, O’Donnell J, Gladden RM, Zibbell JE, Green TC, Younkin M, Ruiz S, Babakhanlou-Chase H, Chan M, Callis BP, Kuramoto-Crawford J, Nields HM, Walley AY. Characteristics of fentanyl overdose – Massachusetts, 2014-2016. Morbidity and Mortality Weekly Report. April 14, 2017

11:  66(14): 382-386.

12:  Mundin G, McDonald R, Smith K, Harris S, Strang J. Pharmacokinetics of concentrated naloxone nasal spray over first 30 minutes post-dosing: Analysis of suitability for opioid overdose reversal. Addiction. 2017

13:  112:1647-1652.

14:  FDA Advisory Committee on the Most Appropriate Dose or Doses of Naloxone to Reverse the Effects of Life-threatening Opioid Overdose in the Community Settings. Joint Meeting of the Anesthetic and Analgesic Drug Products Advisory Committee and the Drug Safety and Risk Management Advisory Committee on October 5, 2016.

KEYWORDS: Opioids, Autoinjector, High Dose Naloxone, Medical, Countermeasure, Drug-delivery, µ Opioid Receptor Antagonist 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: To develop a clinical decision support tool that can be utilized by medics/physicians at Role 3/4 to automatically identify retinal damage after laser exposure. 

DESCRIPTION: Laser injury to the retina does not cause immediate pain therefore it may be undetected until long-term damage to the retina causes vision loss. Currently Role 3 and Role 4 medics and physicians do not have the ability to quickly detect retinal damage after laser exposure. This deficiency reduces quality of care and increases the time to return to duty. A clinical decision support tool to detect laser-induced retinal injury will enable decisions to be made at the Role 3 level and allow physicians to determine the best treatment plan. Lasers are extensively used by the military in designators, rangefinders and guidance systems. Many of these devices operate at wavelengths that are absorbed by the human eye which can produce harmful effects. In addition, high energy laser directed energy weapons have been progressively evolving and there is the possibility that anti-eye laser weapons are being developed. Their use would cause new types of combat casualty which have not yet been extensively experienced, but which will require accurate diagnosis to ensure effective medical solutions. The development of accurate and smart ocular diagnostic technology will expand the capability of clinicians to diagnose and treat ocular injuries induced by laser exposure at the point-of-injury as well as point-of-care. The proposed technology will provide improved field-care capabilities, reduce recovery time of injured warfighters, and help minimize complications of wound healing after trauma or surgery. This test if developed would be a valuable tool in the hands of eye care providers worldwide to assist in the evaluation of laser induced retinal injuries. Payoff: Soldiers will receive appropriate care and will return to duty more quickly. Quality of care will be improved for soldiers who suffer laser-induced retinal injury that may not be detected immediately after exposure without a rapid portable diagnostic tool.  

PHASE I: Develop clinical decision support tool algorithms for rapid analysis of fundus images of the retina before and after laser injury. The retinal images will first go through a rigorous image enhancement phase, image data augmentation, and pixel normalization. Following the enhancement and augmentation processes, algorithms will be developed to identify retinal abnormalities associated with laser damage. Optimize and validate the laser –induced injury detection technology in human fundus images. The end product must achieve high sensitivity and accuracy > 95%. Create protection plan for intellectual property. 

PHASE II: Transition algorithms developed in Phase I. Develop a fully functional prototype. Define the parameters including ease of use, sensitivity and specificity. Develop strategy to acquire FDA approval as a clinical decision support tool. Identify commercial and clinical partners for Phase III. Develop a detailed business plan outlining monetary return on investment within two years of completion of Phase II ( sales, licensing agreements, venture capital, non-SBIR grants). 

PHASE III: Perform experiments as necessary to prepare for FDA review of an IND application. Conduct market analysis. Initiate a Phase I clinical trial to validate utility of a clinical decision support tool to detect laser-induced retinal injury. The diagnostic methodology once developed will be commercialized and made available to the military including forward deployed medics, FSTs and Combat Support Hospitals (CSH). Demand for this device in emergency rooms, ophthalmology and optometry practices worldwide is expected to be high. The portable rapid retinal damage detection tool will also be highly useful to non-military health care providers due to increased use of lasers in the civilian sector, ie fiberoptics and industry. Coordinate with Vision Center of Excellence to facilitate FDA approval and dissemination of the product to military clinicians. 

REFERENCES: 

1: Mainster MA, Stuck BE and Brown JJr. 2004. Assessment of alleged retinal laser injuries. Arch Ophthalmol. 122:1210-1217.

2:  Harris MD1, Lincoln AE, Amoroso PJ, Stuck B, Sliney D. 2003 .Laser eye injuries in military occupations. Aviat Space Environ Med. Sep

3: 74(9):947-52.

4:  Marrugo, A. G., & Millan, M. S. (2011). Retinal image analysis: preprocessing and feature extraction. In Journal of Physics: Conference Series (Vol. 274, No. 1, p. 012039). IOP Publishing.

5:  Grewal, P. S., Oloumi, F., Rubin, U., & Tennant, M. T. (2018). Deep learning in ophthalmology: a review. Canadian Journal of Ophthalmology.

6:  Razzak, M. I., Naz, S., & Zaib, A. (2018). Deep Learning for Medical Image Processing: Overview, Challenges and the Future. In Classification in BioApps (pp. 323-350). Springer, Cham.

KEYWORDS: Laser, Retina, Machine-learning, Deep Learning Architecture 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: To develop a wearable portable stimulator to stimulate the vestibular system and produce immediate improvements in dizziness, balance, gait and overall vestibular function. To enable Service Members to return to duty after suffering injuries that result in vestibular dysfunction. 

DESCRIPTION: Mild traumatic brain injury (mTBI) has been called the “signature injury” of the recent conflicts in Iraq and Afghanistan.1-2 Documentation of vestibular symptoms following these injuries is common, with over 50% of soldiers reporting dizziness post injury and an additional 5-6% complaining of dizziness post-deployment.3 Vestibular damage is not only related to symptoms of dizziness and vertigo but also visual disturbance and imbalance contributing to increased fall risk. Veterans from a wide variety of backgrounds and multiple eras are faced with vestibular impairment and its associated consequences. A recent study of 13,746 OEF/OIF veterans found a 22.4% incidence of vestibular impairment and vestibular dysfunction has been demonstrated in 25% of veterans from the first Gulf War, with commonly reported symptoms including nausea (52%) and dizziness (17%). Correction of dizziness and balance issues remains largely unsolvable from the pharmacy counter. Vestibular rehabilitation, a specialized form of therapy, is the primary treatment strategy to improve symptoms of dizziness related to mTBI/concussion and other pathologies of the inner ear. Limitations with access to skilled rehabilitation providers - both on and off the battlefield - delays treatment, prolongs symptoms and negatively affects an individual’s readiness for duty. Recent research has demonstrated a minimal amount of electrical vestibular stimulation with stochastic resonance can improve stability in patients with vestibular hypofunction.4 Researchers have also shown that a weak electric “noise” can improve balance and motor skills in patients with Parkinson’s disease.5 Building on these research advances, a portable device which can be worn to stimulate the vestibular system using stochastic resonance could significantly enhance the capability to effectively and expeditiously provide relief from vestibular decrements and therefore represents a significant deployment related health solution. Such a solution would directly address a current force capability gap in the ability to proficiently treat and rehabilitate vestibular injury and balance dysfunction. The objective of this topic is to support development of a portable stimulator, about the size of a hearing aid, which can be worn by the end user to deliver a type of vestibular stimulation resulting in relief. A portable stimulator to enhance vestibular function would improve physical function and enable individuals to seamlessly continue duty tasks. If proven effective over a longer term, this device could be made available to veterans or civilians with chronic balance problems, an area where there are currently limited treatments.  

PHASE I: Phase I projects for this topic will conceptualize the technology and identify design specifications. The proposed device should be portable and non-invasive, similar to a hearing aid, and be able to deliver subsensory electrical noise. Studies have shown stability improvements from stochastic resonance using vestibular electrical stimulation when the frequency of stimulation is restricted to a narrow band, less than 5 Hz, while amplitudes of stimulation have ranged from the microampere range to the 1.5-mA range4. Therefore, levels of electrical noise should be low (<2 Hz noise signal), well below a consciously detectable perception, and should be capable of delivering a constant bipolar stimulus in the mA range with minimal user interaction. By the end of Phase I, technical parameters should be solidified and operational functionality established. Clinical experts with insight into relevant patient populations should be consulted during the initial design phase for future clinical studies. 

PHASE II: Based on Phase I design parameters, Phase II work will demonstrate, optimize and validate what constitutes a functional prototype. Phase II projects will demonstrate the ability of the non-invasive, portable device to improve functional capacity (e.g., balance, relieve dizziness) in a population shown to have vestibular impairment. Data obtained in Phase II will provide proof-of-concept that the device will provide abatement of vestibular impairment and improve physical function. Confirmation of no awareness of stimulus should be demonstrated during clinical testing to ensure input noise is at a sub-perceptual threshold. Parameters including device class, general controls, substantial equivalence, and premarket approval will be defined. Clinical experts with insight into relevant patient populations should be consulted as the system is being fully optimized. Potential commercial and clinical partners for Phase III and beyond should be identified. Phase II technical proposals should include a plan for commercial production of the prototype, including potential manufacturing partnerships and funding strategy. The FDA regulatory plan and an outline for approval are deliverables from Phase II. 

PHASE III: Phase III will focus on work that derives from, extends, or logically concludes efforts performed under SBIR agreements. A description of how the technology and device will transition from research to operational capacity should be provided. A proposed DoD customer, such as health care providers at RoC 2 and 3 responding to mTBI in active duty Service Members, and regulatory requirements for these end users should be provided. During Phase III, additional experiments funded by sources other than the SBIR Program will be performed as necessary to ensure FDA IDE approval. A protocol of stimulation parameters that aligns to the Phase II requirements and demonstrates the medical efficacy and feasibility, should be finalized and made commercially viable. A plan for protection of intellectual property should be created and executed. A detailed market analysis will be conducted, an initial application will be submitted for the technology chosen, and a Phase I clinical trial will be initiated. Military application: The effort is relevant to military research efforts in mTBI/concussion. Commercial application: There are currently limited treatments for patients suffering with vestibular loss. This stimulator could easily be translated into a wearable device for other patient populations suffering with vestibular loss and balance impairments. 

REFERENCES: 

1: Hoge CW, McGurk D, Thomas JL, Cox AL, Engel CC, Castro CA. Mild traumatic brain injury in U.S. Soldiers returning from Iraq. N Engl J Med. 2008

2: 358:453‐463.

3:  Schwab KA, Ivins B, Cramer G, Johnson W, Sluss‐Tiller M, Kiley K, et al. Screening for traumatic brain injury in troops returning from deployment in afghanistan and iraq: Initial investigation of the usefulness of a short screening tool for traumatic brain injury. The Journal of head trauma rehabilitation. 2007

4: 22:377‐389.

5:  Terrio H, Brenner LA, Ivins BJ, Cho JM, Helmick K, Schwab K, Scally K, Bretthauer R, Warden D. Traumatic brain injury screening: preliminary findings in a US Army Brigade Combat Team. J Head Trauma Rehabil. 2009 Jan-Feb

6:  24(1):14-23.

7:  Mulavara AP, Fiedler MJ, Kofman IS, Wood SJ, Serrador JM, Peters B, Cohen HS, Reschke MF, Bloomberg JJ. Improving balance function using vestibular stochastic resonance: optimizing stimulus characteristics. Exp Brain Res. 2011 Apr

8: 210(2):303-12.

9:  Khoshnam M, Häner DMC, Kuatsjah E, Zhang X, Menon C. Effects of Galvanic Vestibular Stimulation on Upper and Lower Extremities Motor Symptoms in Parkinson's Disease. Front Neurosci. 2018 Sep 11

10: 12:633. doi: 10.3389/fnins.2018.00633. PMID:30254564.

KEYWORDS: MTBI, Concussion, Vestibular Function, Inner Ear, Portable Stimulator, Balance 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: Current oculomotor assessment practices in clinical bed-side and field environments utilize non-instrumented measures that rely on subjective (Kontos 2018) or observational measures to identify deficits. While these solutions have some limited clinical utility, they lack the capability to appreciate sub-clinical but pathological oculomotor signatures or to localize neuropathology necessary for appropriate diagnosis, management, and disposition of an injured Warfighter. An operationally feasible oculomotor measurement solution which measures physiologic eye movement characteristics would minimize or obviate reliance on subjective measures to diagnose and characterize concussion related oculomotor dysfunction. 

DESCRIPTION: The development of sensitive TBI assessment practices are particularly important in cases where subtle deficits may go underappreciated potentially resulting in premature or inappropriate return to duty decisions which could impact the well-being of the SM, the unit, and potentially adversely impact overall mission success. The use of an instrumented assessment tool capable of characterizing performance in specific oculomotor sub-systems could provide better diagnosis, injury localization, and injury characterization data to guide management, rehabilitation, and disposition decisions in operational environments. Comprehensive oculomotor assessment requires measurement across a broad spectrum of physiologic sub-systems with distinct and integrated neuroanatomy to drive the full range of functional eye movements including rapid re-fixation, smooth pursuit, and gaze stability during head movements (Cheever et al 2018). The assessment of saccades- rapid re-foviating eye movements which direct gaze to specific targets of interest or provide compensatory refoviation to augment gaze stability; smooth pursuit eye movements which allow smooth following of a moving visual target; optokinetic (OKN) eye movements facilitating rapid visual motion processing; and the ability to stabilize gaze during rapid head motion (vestibulo-ocular reflex (VOR): are typically impaired following TBI. At present, comprehensive vestibular and oculomotor testing is limited by the fact that the gold standard video-oculography (VOG) systems are not only unsuitable for field use, they do not control the position of a visual target in space, a feature which is critical to ensure diagnostic accuracy in the measurement of saccadic and smooth pursuit eye movements. 

PHASE I: Develop and provide a prototype of a portable oculomotor assessment (OMA) system consisting of a lightweight goggle head module (< 200 grams) that incorporates binocular tracking cameras, a minimum 9 degree-of-freedom Inertial Measurement Unit, and a laser projection and position control unit. The head module should communicate via wired connection to a lightweight (< 1500 grams) laptop computer or comparable data processing, storage, and display unit (DPU) housed in an impact resistant case suitable for transport in a small rucksack or utility bag. The system’s DPU should support > 3 hours continuous use, data storage, processing, and clinical data display. The laptop/ clinician interface should be loaded with a user-intuitive software interface supporting the execution of proof of concept oculomotor assessment algorithms with demonstrated adherence to the aforementioned technical and output specifications. Required Phase I deliverables include: 1) a research design for engineering a portable oculomotor assessment (OMA) device; 2) A preliminary partially ruggedized prototype system with proof of concept testing and data sufficient to demonstrate the ability to capture, transmit, process, store, analyze, and report functional scores for saccadic (i.e. stationary head and stationary target that instantaneously jumps to a new position and vestibular catch up/ compensatory eye movements), smooth pursuit (i.e. stationary head and moving target), OKN (i.e. stationary head and moving vertical target lines), combined eye/head coordination (moving head and moving target) and VOR (moving head and stationary target) function; 3) demonstrate capability to deliver aforementioned clinical output from the oculomotor assessment system in a clinically useful format to inform clinical decision making relative to normative human performance data.  

PHASE II: Validate the prototype of a compact, modular, ruggedized OMA system that can be used in an operational (field) setting to collect and analyze eye, head and target position motion data and display clinically relevant results of assessment on the laptop unit. The Phase II system should consist of the head module sensors that communicate via wire to the laptop serving as the data storage, processing and display unit. Required Phase II deliverables will include: 1. Validated ruggedization standards should include system’s ability to perform in rainy conditions, vibration tolerant to support transport without damage on military aircraft and vehicles, and impact resistance sufficient to withstand a drop of up to 5 feet. 2. Battery life should be sufficient to support at least 3 hours of continuous use. 3. Mass of head unit and laptop should not exceed 200 grams and 1500 grams, respectively. 4. Recharging should be compatible with existing military power source availability and require no longer than 60 minutes to achieve 80% of full charge. 5. Sampling rate and resolution should be sufficient to reliably characterize the bandwidth of oculomotor, OKN and VOR physiological systems. 6. Algorithms supporting computation of clinical outcome measures should allow for periodic updates by the manufacturer as the state of the science advances to allow integration of emerging assessment conditions using specific measurements. 7. Algorithms to process oculomotor, OKN and VOR data should compute stable, repeatable performance data (saccade size and timing, smooth pursuit gain, OKN gain and time constant, VOR gain during sinusoidal and transient head rotations). 8. Relevant clinical outputs from OMA should include evidence based characterization of oculomotor, OKN and VOR function. A functional score for each physiological system ranging from 0 (complete loss) to 1 (completely normal) will be generated and a single TBI likelihood score will be generated with suggestions to likely cortical region of injury. 9. Outputs should be exportable to a stand-alone monitor, a printable output chart, and in a format that may be saved within a patient’s electronic medical record. 10. Propose Sensitivity and Specificity values using an index score of oculomotor findings that predict presence or absence of central nervous system pathology associated with mild or moderate traumatic brain injury. 11. Deliver a plan for the FDA clearance process and deliver a manufacturing plan.  

PHASE III: Develop and deliver a user’s manual and provisional instructions for use which can support reasonable clinical adoption and sustainment within 10 hours of instruction. Conduct preliminary validation testing to characterize human performance under field conditions in a sample of Active Duty Service Members or a like age, gender and ability matched cohort. Validation of the prototype system should additionally include ability to discriminate healthy control personnel from a cohort with known TBI associated deficits. Based on results of system validation studies, system output should provide an aggregate estimate of duty readiness in the form of a “Green”, “Yellow” or “Red” signal on the clinician interface to indicate how closely patient performance approximates that of the patient’s baseline function and healthy control and duty ready personnel in each oculomotor sub-system. Plans on the commercialization/technology transition and regulatory pathway should lead to eventual FDA clearance/approval. The small business should also consider a strategy to secure additional funding from non-SBIR government sources and /or the private sector to support these efforts. In addition to the stated DoD purpose of assessing injured Service Members with suspected TBI in the training or operational environments, potential civilian customers for this technology may include clinicians or organizations who assess persons with suspected concussion, oculomotor, OKN or vestibular deficits in rural, remote, and underserved regions. Additionally, clinicians assessing pre- and post-injury performance in athletes at risk for acquired head injury in pediatric, collegiate, or professional populations also likely constitute a significant commercial target population.  

REFERENCES: 

1. Kontos AP, Collins MW, Holland CL, Reeves VL, Edelman K, Benso S, Schneider W, Okonkwo D. Preliminary Evidence for Improvement in Symptoms, Cognitive, Vestibular, and Oculomotor Outcomes Following Targeted Intervention with Chronic mTBI Patients. Mil Med. 2018 Mar 1;183(suppl_1):333-338. PMID: 29635578. ; 2. Cheever KM, McDevitt J, Tierney R, Wright WG. Concussion Recovery Phase Affects Vestibular and Oculomotor Symptom Provocation. Int J Sports Med. 2018 Feb;39(2):141-147. PMID: 29190849.

KEYWORDS: Oculomotor Measurement, Concussion Assessment, Vestibular Assessment, Saccadic Assessment 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: To develop, design, and demonstrate new technology or therapies for injured Service Members that will allow patient or caregiver control over urination. 

DESCRIPTION: The Department of Defense has an urgent need for clinical genitourinary technologies that will allow for patients to control their own urine flow. While proposed solutions may be suitable for those who have lost tissue as the result of injury, the primary user will likely be those suffering from neurogenic dysfunction. Urinary dysfunction may be the result of traumatic injury to the lower body or may be neurogenic in nature, resulting from damage or disease of the central nervous system [1]. Traumatic injuries may involve damage or complete loss of tissues necessary for urinary function. Neurogenic damage may not affect specific genitourinary tissues, but can still prevent control over urinary function. Approximately 70-84% of spinal cord injury (SCI) patients will have neurogenic bladder dysfunction (NBD), translating to ~32,000 SCI veterans with NBD [2]. The current clinical standard for treatment of bladder and urinary tract defects is catheterization, which can range from intermittent catheterization, requiring no surgery or permanent implants, to creation of a stoma, bypassing the urethra to empty the bladder directly. Intermittent catheterization is the use, several times a day, of a straight catheter that can be done independently by some patients, or a Foley catheter that allows continuous drainage into a drainage bag worn by the patient. The alternative is creation of a stoma that allows insertion of a catheter. The drawbacks for these procedures are the need for repeated catheter insertion and the need for external collection bags. For Service Members sustaining these injuries, the use of a catheter may be required for decades. There is an inherent risk of infection and catheters may become blocked. Some evidence indicates certain bacteria encourage the development of encrustations that may block the catheter within 24 hours [3]. Catheter related urinary tract infections contribute to more than 40% of nosocomial hospital infections [4]. In addition to these risks, the ongoing costs for lifelong catheterization can be high. The average life span post SCI is over 40 years [5]. With catheters, pads and other supplies costing ~$600/month, this translates to almost $350,000 in a lifetime. For the VA alone, this adds up to over $23 million per year. The ultimate goal of this project is to develop new technologies or therapies that can replace standard catheterization to allow a user to control their own urinary function. The ability to restore urinary function to injured Service Members would improve quality of life, enhance the ability to engage in the activities of daily living, and reduce the need for hospital visits for catheter care. This would be used at Role of Care 4 and with VA populations.  

PHASE I: In the Phase I effort, innovative efforts for restoring urinary function will be conceptualized and designed. Such solutions should be devices, and should not include cellular, tissue or biological components. Phase I efforts can support early concept work (i.e., in vitro studies), or efforts necessary to support a regulatory submission, which do not include animal or human studies, such as stability studies, shipping studies, etc. Proposed technologies should be formulated, and the fabrication or production procedures should be developed for a representative device. The Phase I effort should also include fabrication experiments and benchmarking that demonstrate an adequate capability for meeting the expected challenges in fabricating the proposed technology. It is expected that physical attributes of devices such as patency, user control, urine retention and incontinence, and infection control will be predicted as a function of the material and device structure. Specific milestones for devices include the ability for the user to control urination, to control potential bacterial colonization or infection, and to maintain patency. Proposed solutions should: 1) be gender neutral, 2) be suitable for both urinary tract trauma and neurogenic bladder dysfunction; 3) be both anatomical and functional; 4) replace chronic catheter usage; and 5) be operable by either a patient or a caregiver without specialized training. Proposed solutions should not: 1) rely on nerve stimulation or nerve conductivity to enable function; 2) require diversion of urine to external containers; 3) require specialized clothing that would prevent normal socialization; 4) require frequent readjustments or maintenance by health care personnel; 5) contain components that open within the urine stream; 6) require metals to be in contact with urine; 7) increase the risk of kidney stones; or 8) be solely focused on urine volume sensing. 

PHASE II: In the Phase II effort, a prototype technology or therapy should be fabricated and demonstrated. The performance of the technology should be fully evaluated in terms of patency, user control, urine retention and incontinence, and ability to resist bacterial colonization or infection. The last requirement is especially critical for implanted devices as unresolved bacterial contamination could be life threatening and require removal of an implant. Phase II results should demonstrate understanding of requirements to successfully enter Phase III, including how Phase II testing and validation will support a regulatory submission. Phase II studies may include animal or human studies, portions of effort associated with the same, or work necessary to support a regulatory submission which does not involve animal or human use, to include, but not limited to: manufacturing development, qualification, packaging, stability, or sterility studies, etc. The researcher shall also describe in detail the transition plan for the Phase III effort. The Food and Drug Administration regulatory requirements vary depending on the device classification. As part of the phase II effort, the performer is expected to develop a regulatory strategy to achieve FDA clearance for the new technology. Interactions with the FDA regarding the device classification and an Investigational Device Exemption (IDE), as appropriate, should be initiated. Essential design and development documentation to support FDA clearance, as described in the Quality System Regulation (21 CFR 820.30), should be captured including but not limited to design planning, input, output, review, verification, validation, transfer, changes, and a design history file. The project needs to deliver theoretical/experimental results that provide evidence of efficacy in animal models. The studies should be designed to support an application for FDA clearance. 

PHASE III: During phase III, it is envisioned that requirements to support an application for device clearance from the FDA should be completed. As part of that, scalability, repeatability and reliability of the proposed technology should be demonstrated. Devices should be fabricated using standard fabrication technologies and reliability. The proposal should include a commercialization or technology transition plan for the product that demonstrates how these requirements will be addressed. They include: 1) identifying a relevant patient population for clinical testing to evaluate safety and efficacy and 2) GMP manufacturing sufficient materials for evaluation. The small business should also provide a strategy to secure additional funding from non-SBIR government sources and /or the private sector to support these efforts. Potential DoD funding mechanisms include research programs managed by the Congressionally Directed Medical Research program (CDMRP), which can be found at www.cdmrp.army.mil. Relevant research programs may include the Spinal Cord Injury Research Program (SCIRP) or the Joint Warfighter Medical Research Program (JWMRP). This technology/therapy is envisioned for use in surgical intervention to repair urinary dysfunction in fixed medical treatment facilities. As such, the technology should have both military and civilian applications. Procurement of such technology would be at the discretion of the medical treatment facility. 

REFERENCES: 

1: Panicker JN, et al. Lower urinary tract dysfunction in the neurological patient: clinical assessment and management. Lancet Neurol. 2015 Jul

2: 14(7):720-32.

3:  Dorsher PT, McIntosh PM. Neurogenic Bladder. Adv Urol. 2012

4: 2012:816274. doi: 10.1155/2012/816274.

5:  Lowthian P. The dangers of long-term catheter drainage. Br J Nurs. 1998 Apr 9-22

6: 7(7):366-8, 370, 372 passim.

7:  Bronsema, D. A., Adams, J. R., Pallares, R., & Wenzel, R. P. (1993). Secular trends in rates and etiology of nosocomial urinary tract infections at a university hospital. Journal of Urology, 150, 414-416.

8:  Middleton JW, Dayton A, Walsh J, Rutkowski SB, Leong G, Duong S. Life expectancy after spinal cord injury: a 50-year study. Spinal Cord. 2012 Nov

9: 50(11):803-11. doi: 10.1038/sc.2012.55.

KEYWORDS: Catheter, Urinary Dysfunction, Neurogenic Dysfunction, Genitourinary, Intermittent Catheterization 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: The intent of this SBIR is to develop a medical device that can provide real time analysis of middle ear mechanics, measure the defect to bridge the ossicular reconstruction and measure the tension on the repaired tympanic membrane intraoperatively 

DESCRIPTION: The ongoing conflicts in Asia as result in numerous service members sustaining blast injury to the tympanic membrane. The morbity results in hearing loss and in many patients requires surgical repair. The post-operative hearing result remains less than ideal for our services members. The modern era of tympanoplasty was ushered in by Wullstein and Zollner. Tympanomastoid surgery is quite successful in controlling infection and preventing recurrent disease, with reported success rates in excess of 80–90%. However, it is well recognized that post-operative hearing results are often unsatisfactory, especially in cases with advanced lesions of the ossicular chain or those with nonaeration of the middle ear. As when, the ossicular chain has to be reconstructed, long-term closure of the air-bone gap to < 20 dB occurs in 40–70% of cases when the stapes is intact, and in only 20–55% when the stapes superstructure is missing. Otologic surgeons have a good general appreciation of various anatomical and pathological reasons for failure of tympanoplasty, such as nonaeration of the middle ear, abnormalities of the reconstructed TM and inefficient sound transmission via the reconstructed ossicular chain. However, a quantitative understanding of the acoustical consequences of structural variations of a reconstructed ear is generally lacking. Liston et al., used intra-operative auditory evoked responses during ossiculoplasty and found that minor changes in prosthesis positioning on the order of 0.5–1.0 mm had relatively large effects on hearing (varying up to 20 dB). A clinical observation that postsurgical ears that seem almost identical in structure may demonstrate markedly differing degrees of conductive hearing loss. Small changes in structure have the capacity to have large effects on function. This is also important because small changes in graft and prosthesis position can occur as part of the healing process, which is beyond control of the otologic surgeon. There are major deficiencies in the quest to improve post-tympanoplasty hearing results. There is lack of quantitative understanding of middle ear mechanics, acoustics in the reconstructed middle ear and tension on the repaired tympanic membrane with real time acoustic knowledge. 

PHASE I: Phase I will focus on designing a prototype and determining the technical feasibility of creating a medical device that has the potential to acquire tympanic membrane and middle ear biomechanics perioperatively. The device will include tension measurement on the tympanic membrane intraoperatively, determine ossicular mobility and as well as appropriate length of ossicular prosthesis. Implement the current knowledge of biomechanics of the ear into the device. Perform modeling on per and post-operative surgical outcomes using available technology. Demonstrate product design features and establish performance goals. Provide detailed information on data variables on tympanic membrane and middle ear biomechanics. Estimate the cost of such a device and its usability within the current operative environment within roles 3 and 4 care in the Military Health system. Define the potential risk of using such a device intraoperatively due to technology during development (laser, optical, heat transfer). 

PHASE II: Based on the product from Phase 1 design is to produce a prototype that can then be validated using animal models or cadaveric model. Demonstrate accurate and real-time measures of the tympanic membrane per operatively and post operatively. Validate hearing outcome measures using middle ear biomechanics measurements. The device may integrate with current surgical equipment. There should be consultation with otologic surgeon during design validation. Phase II should outline an FDA regulatory plan. The organization will engage potential partners or consultants for clinical testing.  

PHASE III: During Phase III, additional experiments will be performed as necessary to prepare for FDA approval. It is required that this device to commercialized and made available to the military health system which may include combat trauma acute rehabilitation with levels 3 and 4 of care. A detailed market analysis will be conducted and acquire potential private funding for commercialization. The device will be utilize peri-operatively for surgical planning and intra operatively to improve ossiculoplasty outcomes. 

REFERENCES: 

1: Dornhoffer JL, Gardner E. Prognostic factors in ossiculoplasty: a statistical staging system. Otology and Neurotology. 2001

2: 22:299–304

3:  Mishiro Y, Sakagami M, Adachi O, Kakutani C. Prognostic factors for short- term outcomes after ossiculoplasty using multivariate analysis with logistic regression. Arch Otolaryngol Head Neck Surg. 2009

4: 135:738–41

5:  Liston SL, Levine S.C., Margolis RH, et al. Use of introperative auditory brainstem responses to guide prosthesis positioning. Laryngoscope 1991

6: 101:1009-12

7:  Aarnisalo, A.A., Cheng, J.T., Ravicz, M.E., Furlong, C., Merchant, S.N., Rosows‘ki, J.J., 2009. Motion of the tympanic membrane after cartilage tympanoplasty determined by stroboscopic holography. Hearing Research 263 (1–2), 78–8

8:  Rosowski, J.J., Mehta, R.P., Merchant, S.N., 2004. Diagnostic utility of laser-Doppler vibrometry in conductive hearing loss with normal tympanic membrane. Otology & Neurotology 25 (3), 323–332

KEYWORDS: Ossiculoplasty, Middle Ear Mechanics, Biomechanics, Tympanic Membrane 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: The development of an innovated material/device that can be used to repair tympanic member perforations with limited or no anesthesia. The material can be in the form of a gel, 3d printed material, and other bio material and be used with endoscopes or minimal operative equipment. The material will be employed at level III battlefield of care after injury. 

DESCRIPTION: The last 20 years of armed conflict has resulted in exposure of service members to high intensity sound or blast overpressure waves. The direct consequences of high-intensity noise and blast injuries to the auditory system are hearing loss and tympanic membrane rupture in some cases. Rupture of the eardrum or tympanic membrane (TM) was reported in over 10,000 service members during evaluation at field level III of care. The resultant injury may not receive definitive care for several months post injury until care is accomplished at level IV of care. The result is loss of return to duty status. The injury is a burden to the individual due to hearing loss. Many otologic surgeons contributed to the development and refinement of tympanoplasty techniques. Tympanoplasty surgery is quite successful in the modern area in the operative theater. The plethora of surgical techniques currently employed, the wide variety of autograft, homograft and synthetic materials are available and the continued innovation in biosynthetic materials for otologic use all attest to the fact that reconstructing the tympanic membrane continues to evolve. However, the current cost of performing tympanoplasty in the hospital operating room can be very expensive. The cost of health care continues to increase, the need for performing surgery in the office is now more a common place. We propose to develop a minimally invasive surgical material to repair tympanic membrane perforation that can occur far forward in the battlefield which has the potential to quickly return service members to duty. 

PHASE I: During Phase one, determine and define the material composition that will be tolerated within the middle ear and close/repair a tympanic membrane perforation. The product has no ototoxic potential to both the auditory or vestibular system. Design requirements may include ease of use, minimal equipment or activation process and be delivered minimally invasive. It must be stable, have ease of storage (heat and cold tolerance) and be applied with ease. Demonstration of a prototype is desirable with some early in vitro data. The product should have function and closure rates of tympanic membrane repair that meets the industry standard. The product should be easily removed from the graft site during early healing stages, if necessary, otherwise it should dissolve or incorporate into the healed tympanic membrane. Model key elements of tympanoplasty repair biomechanics, which may include detailed analysis of auditory performance. Design/develop an innovative concept along with limited testing of potential materials. The product will be used by Otolaryngologist at level 3-4 of care. 

PHASE II: Detail analysis of the selected material/device that will include optimal biological properties that are safe and perform equal or better outcomes than standard tympanoplasty. The material should be delivered with minimal surgical tools with no need for an operative suite. The in vivo efficacy will be established. Parameters include ease of use and overall stability across a wide range of conditions. Validation of efficacy will be determined through animal models, histology, and/or other appropriate measures. Clinical experts with insight into tympanic membrane trauma and relevant patient populations should be consulted during optimization and animal validation. Early clinical trials should be considered. Potential commercial and clinical partners for Phase III and beyond should be identified, and a detailed explanation should be provided for how the small business will obtain a monetary return on investment. Phase II should outline an FDA regulatory plan as well consult subject matter experts with military experience. 

PHASE III: During Phase III, additional in vivo experiments will be performed as necessary to prepare for FDA review. It is required that this device to commercialized and made available to the military and as well to the private sector. Clinical trials should be underway. Close communication with military surgeons on the development on the product should be considered. Small business should have a strategy in place to secure funding from the private sector. Device a plan that will bridge the gap between laboratory-scale innovation and entry into a recognized Food and Drug Administration (FDA) regulatory pathway leading to commercialization of the product that will be made available for purchase by the military health system and private sector. 

REFERENCES: 

1: S. N. Merchant · M. J. McKenna · J. J. Rosowski Current status and future challenges of tympanoplasty Eur Arch Otorhinolaryngol (1998) 255 : 221–228

2:  R.T. Chavan, S.M. Ingole and S.N. Birajdar Overview of Tympanoplasty techniques and results Int. J. of Oto and Head and Neck Surg

3:  Carlos R Esquivel, Mark Parker, Kwame Curtis, Andy Merkley, Phil Littlefield, George Conley, Sean Wise, Brent Feldt, Lynn Henselman, Zsolt Stockinger

4:  Aural Blast Injury/Acoustic Trauma and Hearing Loss, Military Medicine, Volume 183, Issue suppl_2, 1 September 2018, Pages 78–82,

5:  Helling ER: Otologic blast injuries due to the Kenya Embassy Bombing. Mil Med 2004

6:  169(11): 872–76.14.

KEYWORDS: Tympanoplasty, Endoscopes, Technique, Hearing, Ototoxicity 

TECHNOLOGY AREA(S): Bio Medical 

OBJECTIVE: The purpose of this SBIR topic is to improve upon haptics devices and integrate them with synthetic (virtual/augmented/mixed reality, or xR) training environments to train hands-on medical procedures to novice trainees with limited medical experience. This will provide medical trainees realistic and anatomically accurate tactile feedback from xR haptic devices, improving training value by building muscle memory and self-efficacy. 

DESCRIPTION: Tactile feedback is critical for accurate medical treatment and consequently medical training. Computer based training is cost effective but is insufficient for developing cognitive and psychomotor skills. Recent training advances have moved beyond keyboard, mouse and display schemes into virtual reality (VR), augmented reality (AR), and mixed reality (MR) environments. However, VR/MR rely on handheld controllers and AR relies on real objects to facilitate interactions. Handheld controllers are intuitive, but they do not allow users to practice procedures to gain the muscle memory for the real world. Augmenting with real objects and simulated patients is realistic but it introduces significant technical challenges in integration and registration. Neither solution delivers a comprehensive, realistic, immersive training experience. Recent advances in haptic technologies can help overcome these limitations by forcing trainees to realistically interact with the environment without sacrificing the flexibility of AR/VR/MR training. With advanced haptic delivery systems, physical sensations are mapped to the trainee’s visual and spatial perception within the environment. These combined technologies foster natural trainee interactions to perform medical procedures in the environment. Rather than moving a controller and clicking a trigger to grab a virtual object, users can reach out and grasp, feel, and manipulate virtual entities, just as they would with a real object. This research proposes to refine the haptic delivery technologies by reducing the hardware footprints and reducing costs while expanding utility within a widely used military training environment for Tactical Combat Casualty Care (TC3). Prototype haptic technologies have been integrated into a virtual training application with promising results. Users can perform a needle chest decompression and apply a tourniquet onto virtual patients using fine motor skills to manipulate the medical equipment. This proposed effort will expand the haptics-based training scenarios inside a virtual training simulation to include additional medical tasks, and to integrate soldier tasks such as weapon manipulation. The intent is to demonstrate the applicability of advanced haptics to interact with soft entities (patients) and hard entities (weapons) within a warfighting simulation in the Army’s new Synthetic Training Environment.  

PHASE I: Phase I will consist of research into emerging haptic devices and determine their ability to replicate the tactile feedback of one or more basic Tactical Combat Casualty Care (TC3) skills that require both gross motor skills (e.g., palpating an anatomical landmark) and fine motor skills (e.g., IV insertion). Applicability of the chosen haptic device to integrate with one or more government-funded virtual training simulations should be taken into consideration. During this phase, the offeror should focus on portions of the human hand for haptic delivery. As a proof of concept, the physical footprint of any equipment delivered will not be limited. The intent of this phase is as follows: 1) to produce a lab-based initial proof of concept and/or prototype for the haptic delivery system; 2) to provide considerations for interoperability with future and existing military medical training systems (e.g. AR/VR/MR training environments, physical medical training devices and patient simulations (rigid, semi-rigid, and soft structures), the Army Synthetic Training Environment, and any possible combinations of these); 3) to provide a detailed evaluation of appropriate sensing technologies to merge the virtual training environment with the physical training environment; and 4) to develop a detailed set of initial scenarios for the haptic delivery system designed to demonstrate items 2 and 3. Deliverables from this phase must demonstrate the feasibility of the concepts described within this topic. Upon completion, the performer will submit a final report including these analyses, and provide an initial demonstration describing the current state of development, along with details for the Phase II development plan. 

PHASE II: Phase II will consist of improvements to the prototype that supports haptic training for needle chest decompression and tourniquet application, as well as other TC3 tasks (e.g. operating or reloading a weapon) in an xR environment, exhibiting highly accurate fine and gross motor movements. The offeror will iteratively develop, demonstrate, and validate prototype units capable of haptic simulations for a variety of procedures that are common in point of injury care and care under fire. Building off of work in Phase I, the offeror will develop haptic models for a variety of structures to be used in relevant TC3 training scenarios, including rigid (rifle components, scissors, scalpels, etc.) and soft structures (surface tissues and deep tissues, tourniquets, gauze, etc.). These haptic models must be integrated into demonstrations of training solutions across the xR spectrum. Engineering design improvements will minimize the overall footprint and logistical cost of the system, while also maximizing haptic fidelity and expanding sensitivity to more areas of the hand as required. Phase II will include opportunities for demonstrations to key military and commercial stakeholders, both at the midpoint and during the final stages of development. Phase II will culminate in a usability evaluation and a training effectiveness evaluation of all features of the prototype system(s) with a relevant military training population, to be determined by key military stakeholders. Offerors looking towards a Phase III for development will complete Phase II by describing initial efforts to identify and secure potential military and commercial clients, as well as initial considerations for productization, including but not limited to affordability, manufacturability, durability, failure rates, and reparability, within the context of the work completed during Phase II and any challenges encountered. 

PHASE III: Contingent upon available funding and a successful conclusion of Phase II work, in this phase the offeror will have developed a commercially viable, easy to use haptic delivery system capable of being used with a variety of military medical training systems, and also capable of satisfactorily merging the virtual training environment with the physical training environment. The offeror will dedicate Phase III towards optimizing affordability, manufacturability, durability, failure rates, reparability, and other productization considerations, including open-source software tools and authoring capabilities. Phase III must also establish solid pathways towards transition and commercialization, pursuing both DoD and commercial markets. This haptic delivery system has broad applications for providing military medical training, but other types of medical training should be considered as well. The offeror will demonstrate the product at one or more potential “customer” sites. All demonstrations, dates, and times at military training sites will be selected by the Synthetic Training Environment Cross Functional Team under Army Futures Command. Phase III will consist of additional refinements to the prototype unit(s) developed under Phase II. Building upon the Phase II work, Phase III will finalize research and development to integrate Point of injury care procedures will be extended to include additional deep tissue surgical procedures. Additional work will involve establishing complete integration (hardware and software) into the broader Army Synthetic Training Environment, as well as related environments from other DoD training programs. In addition to TC3 tasks, the prototype system shall haptically simulate additional, relevant, complex warfighter tasks. Phase III will culminate in a usability evaluation and a training effectiveness evaluation of all of the features of the prototype system(s) with a relevant military training population. The offeror will coordinate with a military and/or commercial partner to ensure compliance with all applicable DoD/service-specific certifications required for full transition. 

REFERENCES: 

1: Fulkerson, Matthew, "Touch", The Stanford Encyclopedia of Philosophy (Spring 2016 Edition), Edward N. Zalta (ed.), URL = <https://plato.stanford.edu/archives/spr2016/entries/touch/>.

2:  Hauck, R. (2017). Virtual surgery and orthopaedic surgery: towards training using haptic technology (Doctoral dissertation, University of Nottingham).

3:  Linde, A. S., Caridha, J., & Kunkler, K. J. (2017). Incorporating Present Knowledge in SkillsDecay into Future Augmented Reality Haptic Medical Simulation Training Interfaces. MHSRS Abstract# MHSRS-17-0520.

4:  Mathur, A. S. (2015, March). Low cost virtual reality for medical training. In Virtual Reality (VR), 2015 IEEE (pp. 345-346). IEEE.

KEYWORDS: Haptics, Virtual Simulations, Synthetic Training Environment, Tactical Combat Casualty Care 

TECHNOLOGY AREA(S): Air Platform, Materials, Weapons, Nuclear 

OBJECTIVE: OBJECTIVE: Improve product availability and increase competition through the development of Source Approval Requests (SAR) by small business manufacturers for National Stock Numbers (NSNs) with government provided technical data or through the Reverse Engineering (RE) of a technical data package. If DLA has adequate technical data available, the small business manufacturer will utilize the technical data to develop a SAR package. If the technical data is not available or inadequate, the small business will conduct relevant research and reverse engineering resulting in the development of the technical data package (TDP) as well as a SAR. The intent is that the participating small business manufacturer, once the SAR package is approved by the Engineering Support Activity (ESA), will be responsive to future solicitations as well as participate in the development of additional SARs for technically related NSNs. 

DESCRIPTION: DESCRIPTION: The DLA Nuclear Enterprise Support Office (NESO) was established to position the Agency to be fully responsive to the needs of the United States Air Force and U.S. Navy nuclear communities. The sole mission of the office is to synchronize DLA’s enterprise wide support to the nuclear enterprise and engage strategically with DLA customers. Through partnerships with the small business industrial base, DLA will augment existing sources of supply to enhance life-cycle performance, product availability, competitive pricing as well as ensure effective logistics support to the nuclear enterprise. This program is restricted to DLA managed NESO items where sources of supply are scarce and is in use to incentivize small business participation to address specific weapon system requirements as well as provide small manufacturers the opportunity to build a mutually beneficial relationship with DLA. A SAR package is an assembly of information required of a prospective new supplier of a Critical/Weapon System Item (NSN). A SAR package contains all technical data needed to demonstrate that the prospective contractor can competently manufacture the Critical/Weapon System Item to the same level of quality or better than the system prime contractor, major subsystem contractor, or initial Approved Source (OEM). There are SAR Guides with templates and charts that explain the process. The guide, charts, checklists, and templates can be found via the internet at the referenced link 1. The list of candidate parts is posted on the DLA Small Business Innovation Program (SBIP) site http://www.dla.mil/SmallBusiness/SmallBusinessInnovationPrograms Specific parts may require minor deviations in the process dependent on the Engineering Support Activity (ESA) requirements. Those deviations will be addressed post award. Participating small businesses must have a Commercial and Government Entity (CAGE) code and be Joint Certification Program (JCP) certified in order to access technical data if available. Refer to “link 2” below for further information on JCP certification. Additionally, small businesses will need to create a DLA’s Internet Bid Board System (DIBBS) account to view all data and requirements in C Folders. Refer to “links 3 and 4” below for further information on DIBBS and C Folders. All available documents and drawings are located in the C Folder location “SBIR_192”. If the data is incomplete, or not available, the effort will require reverse engineering. 

PHASE I: The innovation research goals of Phase I are to provide small business manufacturers an opportunity to qualify as an Approved Source for one or more of the NSNs specifically identified in this BAA. In this phase, manufacturers will request SAR approval from the applicable Engineering Support Activity (ESA) and will submit a Gantt chart detailing the steps and timing to complete the TDP, SAR, through the beginning state of Low Rate Production (LRIP) of the NSN(s). In addition, it is encouraged that manufacturers and engineers consider innovation opportunities for the identified component for the potential for cost reduction, extended life cycle, and improvement of the performance of the component. The culmination of this research will provide the basis for the business case to be included in the final report. The NESO team selected the list of items and associated details to address the needs of the Nuclear Enterprise to sustain critical weapons systems as described below. Proposals may include all or a subset of the NSNs listed at http://www.dla.mil/SmallBusiness/SmallBusinessInnovationPrograms. Multiple proposals may be submitted for this topic providing that the proposals address unique NSNs. Proposal costs should be generated based on the level of effort and not the maximum available dollars to be competitive. 

PHASE II: Based on the results achieved in Phase I, DLA NESO will decide whether to continue the effort based on the technical progress, potential for authorization to participate as an Approved Source, and feasibility of the manufacturer’s business case. The goal of Phase II is to obtain authorization to participate as an Approved Source, conduct product qualification, and test as appropriate, and achieve Low Rate Production for the specific NSN in future procurements. If the part identified is already in production as a result of Phase I, the Phase II may be used to create additional manufacturing capacity to meet demand and/or pursue SARs for other DLA managed items.  

PHASE III: At this point, no specific funding is associated with Phase III. Progress made in PHASE I and PHASE II should result in the manufacturer’s qualification as an approved source of supply enabling participation in DLA procurement actions. COMMERCIALIZATION: The manufacturer will pursue commercialization of the various technologies and processes developed in prior phases through participation in future DLA procurement actions on items identified with this BAA. 

REFERENCES: 

1: DLA Aviation SAR Package instructions. DLA Small Business Resources: http://www.dla.mil/Aviation/Business/IndustryResources/SBO.aspx

2:  JCP Certification: https://public.logisticsinformationservice.dla.mil/PublicHome/jcp/default.aspx

3:  Access the web address for DIBBS at https://www.dibbs.bsm.dla.mil/default.aspx, select Tech Data Tab and Log into c-Folders. This requires an additional password Filter for solicitation "SBIR_192"

4:  DLA Small Business Innovation Programs web site: http://www.dla.mil/SmallBusiness/SmallBusinessInnovationPrograms.

KEYWORDS: NESO Parts 

TECHNOLOGY AREA(S): Materials, Sensors, Electronics 

OBJECTIVE: Develop and validate method/s to measure the local temperature of a specimen of interest while being imaged inside a Transmission Electron Microscope (TEM) to decipher the root cause of defects triggering failure in ICs. 

DESCRIPTION: Characterization of electronic devices via TEM has been an indispensable technique in semiconductor manufacturing. TEM functions through the interaction of electrons with materials resulting in high spatial resolution imaging and spectroscopy of samples under study. To maintain the functionality of DoD microelectronics systems, it is essential to perform a thorough investigation of device failure, which often involves localizing defects on a sub 10 nm scale using TEM. Furthermore, successful semiconductor device fabrication requires systematic reliability testing, which relies on utilizing the TEM in conjunction with analytical techniques to identify the failure mechanism/s associated with malfunctioning electronic devices. In general, TEM allows for the direct observation of materials properties; e.g., defects, which could either impair or improve functionality of samples ranging from electron devices and exotic materials to biological samples. However, electron beam induced damage caused by elastic and/or inelastic scattering of electrons interacting with matter inside the TEM is inevitable. Distinguishing defects caused by the electron beam from the ones intrinsic to the sample under study can be a difficult task; therefore, developing methods to evaluate the root cause of the identified defects in devices is necessary. Electron beam damage can take on any of the following forms [1]: i) Radiolysis or ionization ii) Knock-on or sputtering causing displacement of atoms iii) Heating, which can lead to matter transformation. Though beam damage to the sample is undesirable in most cases, we can utilize it to emulate radiation damage speed-up inside the TEM. Additionally, in-situ TEM studies can be utilized to study the failure mechanisms responsible for malfunctioning and low reliability of semiconductor devices. It is important to measure the sample temperature inside the TEM precisely while imaging as it can influence interpretation and measurement analysis; e.g., determining the lattice constant at room temperature. [2] It is generally difficult to experimentally measure the sample temperature as it depends on various parameters: 1) beam energy, current density and size, 2) sample thickness, and 3) thermal conductivity of the sample. [1, 3-4] Thus, a method integrated with the TEM to measure the sample temperature directly and in real-time is required. Potential methods capable of in-situ sample temperature measurements inside the TEM include [5]: i) bulk plasmon measurement based on electron energy loss spectroscopy (EELS) ii) Raman scattering iii) parallel beam diffraction iv) thermo-reflectance. However, these methods have limitations ranging from sensitive analysis procedure and narrow applicability (i.e., only to specific samples) to low spatial resolution, and therefore do not provide accurate temperature measurement with high spatial resolution (sub 10 nm). Hence, the performer is expected to evaluate, develop and/or integrate methods to measure the sample temperature inside the TEM with high spatial resolution (sub 10 nm) and high accuracy (1°C) to precisely evaluate defects in materials. 

PHASE I: Perform a feasibility study for integrating systems and/or methods with a TEM to allow local temperature mapping and distinguish the effect of electron beam radiation damage from intrinsic material structure of the sample. Specifically, conduct research on techniques of interest to evaluate the feasibility of measuring the sample temperature inside the TEM as described above. The proposed technique should be capable of measuring local sample temperature with high spatial resolution, high accuracy and in real-time. The goal of this technique development is to image the local temperature of the sample of interest inside a TEM quantitatively while adhering to the following constraints: ‒ Spatial resolution: ≤ 10 nm ‒ Temperature sensitivity detection (ΔT): 1 °C ‒ Temporal resolution: Real-time temperature measurement within dwell time If any of the above constraints cannot be met the feasibility report shall include all the rational and relevant research. 

PHASE II: Phase II will result in building, testing and delivering a prototype of the method developed in phase I. Prototype demonstration will include numerous testing data on two main types of experiments in both scanning and parallel TEM operation modes. The first experiment type entails post-mortem analysis of integrated circuits (ICs) to investigate defects. Explicitly, the system will deliver data regarding the influence of beam heating on defect analysis of ICs through quantitative temperature mapping. The second experiment type includes in-situ TEM studies on failure mechanisms of ICs. There is no thermocouple inside TEM to measure the sample temperature and not all TEM sample holders have the capability to measure the approximate sample temperature after the application of external stimuli, which could be heat or electric field or laser. [6] The four main failure mechanisms of ICs include: i) time-dependent dielectric breakdown (TDDB), ii) electromigration (EM), iii) hot carrier injection (HCI) and iv) negative bias temperature instability (NBTI). The performer can select any of the above failure mechanisms to deliver related data pertaining to temperature measurement of the sample of interest. In the second experiment type, the cause of temperature rise of the sample is due to both external stimuli, utilized for studying the failure mechanism, and beam irradiation. 

PHASE III: Phase III will result in the expansion of the prototype system in Phase II into a tested pre-production system, which entails a technique integrated with a TEM for local temperature mapping of samples. This system can be utilized for evaluating failures of ICs both in commercial and government sectors. Additionally, the proposed system enables better understanding of the root cause of defects responsible for failure/s and provides insights regarding various failure mechanisms affecting the functionality and the reliability of semiconductor devices, respectively. Furthermore, the system could have the potential to measure the temperature of samples other than ICs; e.g., biological samples and oxides used for high temperature superconductivity study. 

REFERENCES: 

1: D. B., Williams & C. B., Carter. Transmission Electron Microscopy. New York, NY: Springer Science, 2009.

2:  F. Niekiel, et al., Local Temperature Measurement in TEM by Parallel Beam Electron Diffraction, Ultramicroscopy 176 (2017) 161-169.

3:  R.F. Egerton, et al., Radiation Damage in the TEM and SEM, Micron 35 (2004) 399-409.

4:  D. J. Smith, et al., Exploring Aberration-corrected Electron Microscopy for Compound Semiconductors, Microscopy 62 (2013) S65-S73.

5:  M. Mecklenburg, et al., Nanoscale Temperature Mapping in Operating Microelectronic Devices, Science 346 (2015) 629-632.

6:  S. Hihath, et al., High speed direct imaging of thin metal film ablation by movie-mode dynamic transmission electron microscopy, Scientific Reports 6 (2016), Article number: 23046.

KEYWORDS: TEM, Temperature Mapping, Beam Damage, Failure Analysis, Semiconductor Devices, ICs 

TECHNOLOGY AREA(S): Info Systemssensors, Electronics, Battlespace 

OBJECTIVE: Design and implement machine learning or machine vision technologies to determine the authenticity and security of microelectronics parts in weapon systems. These technologies may be purely software based or include a hardware component. 

DESCRIPTION: Determining the authenticity and security of microelectronics parts in weapons systems is of the upmost importance to the Department of Defense (DoD) [1,2]. Counterfeit and modified electronics pose a significant threat to the warfighter [1]. Although there has been much progress in detecting counterfeit parts [3], the sophistication of the counterfeits continue to evolve to evade detection. This evolution includes the introduction of cloned components [4] which are often undetectable through normal anti-counterfeit measures, including electrical testing. The Defense Microelectronics Activity (DMEA) is looking to apply machine learning and machine vision technologies as part of a detection or authentication scheme that will make avoiding detection impractical or even impossible. Such a scheme is only useful if implemented; therefore, it is essential for any proposed technology to be both cost and time efficient. There are many potential areas that these technologies can address, such as: validating golden units, classifying side channel signatures of microelectronics, automating general counterfeit detection, creating signatures for individual microelectronics, etc. The commercialization and technical evaluation for proposals will include the practicality of implementing the technology in the microelectronics supply chain. 

PHASE I: Conduct research on machine learning and machine vision technologies to determine the authenticity and security of microelectronic parts in weapon systems. These technologies may have an associated hardware component and may be part of broader system to secure the supply chain for weapon systems. The end product of Phase I is a feasibility study report, in which the following must be specified: 1) A clear description of the technology and how it is applied. 2) The computer hardware required to execute any required software program (e.g., workstation, cloud, GPUs, etc.). 3) Any associated hardware required as part of the technology solution (e.g. fixturing, sensors, cameras, tools, etc.). 4) A clear description of any required training sets or other requirements for the effective implementation of the technology. 5) A clear description of how to incorporate the technology into the process of developing, transporting, and inserting microelectronics into weapon systems to determine their authenticity and security. This description should include a business case for the time and cost to incorporate the technology. 

PHASE II: Develop a prototype of the Phase I concept and demonstrate its operation. Validate the performance in a way that realistically demonstrates how the technology would be deployed. This demonstration will include scalability of the technology in terms of capacity, cost, and time. 

PHASE III: There may be opportunities for further development of this innovation for use in a specific military or commercial application. During a Phase III program, the contractor may refine the performance of the design and produce pre-production quantities for evaluation by the Government. The proposed technology will be applicable to both commercial and government fields that require an added level of security for their microelectronics parts. Government applications include anti-counterfeit applications and acquisition processes for microelectronics parts for weapon systems and other critical systems. Commercial functions include the secure acquisition of microelectronics parts for critical applications such as medical, automotive, telecommunication, etc. 

REFERENCES: 

1: U.S. Senate Committee on Armed Services, "Inquiry into Counterfeit Electronic Parts in the Department Of Defense Supply Chain," May 2012. [Online]. Available: https://www.armed-services.senate.gov/download/inquiry-into-counterfeit-electronic-parts-in-the-department-of-defense-supply-chain.

2:  DARPA, "Supply Chain Hardware Integrity for Electronics Defense (SHIELD)," February 2019. [Online]. Available: https://www.darpa.mil/program/supply-chain-hardware-integrity-for-electronics-defense.

3:  SAE Aerospace Standard, "Test Methods Standard

4:  General Requirements, Suspect/Counterfeit, Electrical, Electronic, and Electromechanical Parts AS6171A," April 2018. [Online]. Available: https://www.sae.org/standards/content/as6171a/

5:  Government Accountability Office, "Counterfeit parts: DoD needs to improve reporting and oversight to reduce supply chain risk," GAO-16-236, Feb. 16, 2016. [Online]. http://www.gao.gov/assets/680/675227.pdf

KEYWORDS: Software, Machine Learning, Electronics, Anti-Counterfeit, Microelectronics, Machine Vision 

TECHNOLOGY AREA(S): Sensors, Electronics, Battlespace 

OBJECTIVE: Develop a semiconductor device Fault Isolation tool that works across a wide range of technology processes. 

DESCRIPTION: Infrared (IR) Microscopes are used in the Failure Analysis (FA) and Fault Isolation (FI) of silicon-based semiconductor devices because of the fact that silicon is transparent to near-IR (NIR) light. Some of these microscopes use Charge-Coupled Device (CCD) cameras that are specifically designed for the NIR wavelengths, and others use a NIR wavelength laser with a scanner. These tools are used to find specific areas of interest, and are particularly effective when using them to find faults on Flip Chip, or Controlled Collapse Chip Connection (C4) devices where the bond pads are connected directly to the package substrate, leaving the bulk silicon (backside) fully exposed. A common alternative to Flip Chip is wire-bonded devices where the bulk silicon of the device is mounted to the package and bond wires attach the bond pads to a lead frame on the package. Most of the State-of-the-Art (SOTA) FI tools have been developed specifically for Flip Chip devices. This presents a challenge when attempting to use these SOTA FI tools with legacy wire-bonded devices, or even unpackaged C4-based devices (full/partial wafers, bare die, etc.). One of the requirements for these SOTA FI tools is that the device must be electrically stimulated in order to detect the faults (open circuits, short circuits, etc.) When inspecting a wire-bonded device using these tools, one must inspect the frontside, as that is the only side that is accessible. This limits the FI capabilities to detecting faults that occur on the topmost metal layer, and any faults present in the circuitry below is blocked by the preceding layers above. If instead, the device could be stimulated (e.g. micromanipulator probing, probe card, etc.) from the frontside while still allowing the FI tool to access the backside of the device, the FI capabilities would be improved greatly, allowing the tools to be used with both packaged and unpackaged parts. Most of the SOTA FI tools include a Solid Immersion Lens (SIL) that makes physical contact with the device under test (DUT), providing high magnification (350X) with a very high Numerical Aperture (NA) (>2.5). One of the main challenges is handling the devices. When inspecting a device with the SOTA FI tools, typically they are backside-thinned such that the remaining silicon thickness (RST) is 100µm or less, depending on the tool. With most of the bulk silicon removed, there is little structural support remaining; this results in a very fragile device. When using a SIL on a Flip Chip device, the package substrate provides the structural support needed to prevent damaging the thinned DUT. The innovative development of a tool that can be used to probe the frontside bond-pads of a device while allowing for simultaneous backside inspection is desired. DIRECT TO PHASE II: DMEA will only accept Direct to Phase II proposals. 

PHASE I: Perform a study on different methods for electrically stimulating various semiconductor microelectronic devices while allowing for access to the backside for inspection. The end result of Phase I is a feasibility study report, which demonstrates all the rational justifications for studying the proposed technique. The report will explicitly addresses the following items: 1. The developed tool shall be compatible across a wide range of semiconductor microelectronics devices, including but not limited to wire-bonded, Flip Chip, full wafers, bare die, etc. 2. The developed tool shall be capable of electrically stimulating the DUT from the frontside while simultaneously being able to inspect the backside of the device with a backside inspection tool without blocking photoemission transmission. 3. The developed tool shall be capable of precisely and accurately positioning each probe from the top side. The feasibility study shall identify the characteristics of the probing system, including but not limited to probe tip sizes, accuracy, precision, maximum number of probes (micromanipulators and probe card), etc. 4. The developed tool shall be capable of allowing the use of a SIL on the backside of the DUT while being electrically stimulated. 5. The developed tool shall be capable of moving all of the probes together independently from the DUT, such the probing orientation can be used across multiple devices without moving each probe one by one while maintaining the same Field of View on the backside inspection tool. The feasibility study shall identify the travel range limitations of the stage. 6. The developed tool shall be capable of docking to DMEA’s backside inspection FI tool interface without exceeding 100lbs. 7. The developed tool shall be capable of interfacing with Industry standard Integrated Circuit (IC) electrical testing equipment. 8. The feasibility study shall identify the DUT size limitations, including but not limited to both the upper and lower limits for sample size, thickness, etc. 9. The feasibility study shall identify the DUT feature size limitations, including but not limited to the smallest bond-pad size that can be electrically stimulated by the system, bond pad pitch, bond pad spacing, etc. 10. The feasibility study shall identify the minimum force required to be applied by the electrical stimulation system in order to maintain electrical connectivity without damaging a thinned device for various thicknesses less than or equal to 100µm, including but not limited to 100µm, 50µm, 25µm, 10µm. 11. The feasibility study shall identify the DUT mounting methodology and any associated transmission loss percentage induced by the DUT mounting methodology. Deliver a report of research and innovation, including a notional list of possible components, a list of all the facility requirements and a program plan for system development. If any of the above restraints cannot be adhered to, the report must include relevant research and rationale. If adhering to the above restraints is possible, but not financially feasible, the report must include relevant research and rationale. FEASIBILITY DOCUMENTATION: Offerors interested in participating in Direct to Phase II must include in their response to this topic Phase I feasibility documentation that substantiates the scientific and technical merit and Phase I feasibility described in Phase I above has been met (i.e. the small business must have performed Phase I-type research and development related to the topic, but from non-SBIR funding sources) and describes the potential commercialization applications. The documentation provided must validate that the proposer has completed development of technology as stated in Phase I above. Documentation should include all relevant information including, but not limited to: technical reports, test data, prototype designs/models, and performance goals/results. Work submitted within the feasibility documentation must have been substantially performed by the offeror and/or the principal investigator (PI). 

PHASE II: Based on the aforementioned study and applicable innovation, produce a fully functioning prototype that adheres to all the constraints listed above. Test the prototype and deliver along with at least four (4) samples. Two (2) of the sample should represent the smallest and thinnest sample size the system is capable of supporting and should show the process repeatability between both samples. The other two (2) samples shall represent other sample cases, demonstrating the wide range of devices supported and the flexibility/universality of the system. Deliver a complete Bill of Materials (BOM), including all components used, manufacturers, part numbers, quantities, technical datasheets, facility requirements, and CAD drawings for each component and a complete CAD assembly for the completed prototype. 

PHASE III: There may be opportunities for further development of this system for use in a specific military or commercial application. During a Phase III program, offerors may refine the performance of the design and produce pre-production quantities for evaluation by the Government. The Backside Inspection Frontside Electrical Stimulation System would be applicable to both commercial and government semiconductor device research and FA. Government applications include FA and FI of semiconductors. Commercial applications include FA and FI of semiconductors. 

REFERENCES: 

1: Dan Bockelman, et al. Multi-Point Probing on 65nm Silicon Technology using Static IREM-based Methodology. ISTFA 2005.

2:  John H. Lau. Status and Outlooks of Flip Chip Technology. ASM Pacific Technology. 02/20/2017

3:  Kenneth Krieg, et al. Electrical Probing and Surface Imaging of Deep Sub-Micron Integrated Circuits. ISTFA 1999.

4:  M.S. Wei, et al. Sample Preparation for High Numerical Aperture Solid Immersion Lens Laser Imaging. ISFTA 2014.

KEYWORDS: Fault Isolation, Failure Analysis, Electrical Stimulation, Probing 

TECHNOLOGY AREA(S): Chem Bio_defense, Materialsweapons 

OBJECTIVE: DTRA seeks an A.I. enabled operating system to be applied to energetic materials (explosives) testing chambers for a modern, efficient, and rigorous capability to quickly and thoroughly characterize such materials and provide a database with automated analytical capability to show, e.g., historical performance trends, performance comparisons, variations in conditions between data points, estimate scaling performance, estimate data point error, etc. 

DESCRIPTION: The envisioned product should be able to communicate with and control a wide variety of instrumentation and diagnostic systems such that environmental, calibration curves, and other metadata information can be automatically logged and correlated with the data from measuring the explosive material performance. Such instrumentation may include both analog and digital components such as thermocouples, pressure transducers, spectrometers, cameras, oscilloscopes, etc. Data from all connected systems should be, or be able to be, automatically correlated with time and space information. The system should be able to monitor connected systems to allow, e.g., self-health checks or report when recalibration may be required. The developed operating system should allow automated or user-defined sequencing and test procedures to be defined and applied. The system should be able to provide automated analysis of tests to provide immediate feedback such as whether a test article fell within an expected performance range or whether all instrumentation captured an event successfully. Additionally the system should eventually be able to suggest appropriate testing to fill in data gaps in its database using rules such as from Design of Experiments. Modern data visualization techniques, such as virtual or augmented reality, should be supported such that events could be replayed with data layers from non-visual sensors available for overlay (e.g. be able to see a color layer representing pressure or temperature overlaid on a 3D movie of the event). More-over the system should be able to apply intelligent analysis to the database developed in order to predict baseline performance of new compounds, scaling performance of tested compounds, etc. The developed product should not be specific to a single chamber, but should instead be able to be applied to various chambers given appropriate setup. 

PHASE I: Design the intelligent operating system. Identify key hardware and software components and how they may be sourced or developed. Identify any technical or integration risks. Obtain or prototype significant or high risk components for testing and produce an analysis of alternatives if needed. Identify a particular chamber and instrumentation suite to be used with a phase 2 prototype system. 

PHASE II: Based on Phase I findings develop the initial system around a selected chamber and instrumentation suite. Demonstrate the performance of each component of the system (automated testing, data collection, automated analysis, data visualization, predictive analysis, etc.) with known compounds and compare results to expectations from historical data. 

PHASE III: Continue to develop and refine the Phase II product into a useful asset for DTRA. Adapt the product application for DTRA specific testing to include development or application of safety and security measures as required. Populate the database with quality data on DTRA specified compounds and confirm all of the autonomous and AI enabled capabilities are trained and working appropriately. Investigate commercialization avenues that could include other government agencies, national labs, research institutes, and defense contractors. 

REFERENCES: 

1. Mader, Charles & Crane, S.L. & Johnson, J.N. (1983). Los Alamos Explosives Performance Data.; 2. Dobratz, B.M. (1981) LLNL Explosives Handbook Properties of Chemical Explosives and Explosive Simulants. Lawrence Livermore Laboratory UCRL-52997.; 3. Nazarian, A. & Presser, C. (2013). Forensic analysis methodology for thermal and chemical characterization of homemade explosives. Thermochimica Acta, 576, 60-70.; 4. Maines, W.R., Kittell, D.E., and Hobbs, M.L. (2018). Combined Mini-Cylex & Disk Acceleration Tests in Type K Copper. Propellants, Explosives, Pyrotechnics, 43, 506-511.; 5. Le, Q. & Zoph, B. (2017). Using Machine Learning to Explore Neural Network Architecture. Google AI Blog, https://ai.googleblog.com/2017/05/using-machine-learning-to-explore.html.; 6. Chu, T. & Funke, M. (2019). The AI database is upon us. IBM Blog, https://www.ibmbigdatahub.com/blog/ai-database-upon-us.; 7. Anadiotis, G. (2018). GPU databases are coming of age. Big on Data Blog. https://www.zdnet.com/article/gpu-databases-are-coming-of-age/

KEYWORDS: Autonomy, Machine Learning 

TECHNOLOGY AREA(S): Air Platform, Info Systems, Ground Sea 

OBJECTIVE: To develop advanced artificial intelligence (AI) for competitive offensive as well as defensive unmanned systems to counter hostile threats that lead to degraded performance. This topic seeks development of (1) computational methods that use a single reinforcement agent to solve complex, multi-task problems and (2) simulated learning environments that can be used to train as well as to evaluate putative solutions. 

DESCRIPTION: AI has recently been described by experts within the U.S. Departmet of Defense Autonomy Community of Interest (COI) as “the next arms race”. The implications of adversarial use of AI and its successively greater incorporation into unmanned and autonomous systems remain both unknown and a considerable source of apprehension. Exponential growth in the C-UAS industry, for example, points to mounting concerns regarding use of drones in civilian and military settings, and particular concern surrounds the potential for highly coordinated and disruptive attacks mediated by groups of small (i.e., “swarming”) unmanned systems. Increased domestic and global investment in such technologies also enhances the probability that swarming systems and other C-UAS technologies could be exploited by the adversary to thwart U.S. military operations for which UAS are preferentially used. Outcompeting increasingly intelligent unmanned vehicle technologies to ensure mission completion, especially where communications to a human operator are limited or non-existent, requires insertion of sophisticated computational architectures that provide means to autonomously perform new and different tasks while operating under rapidly changing conditions such as system failures, variable weather conditions, and adjustments to mission based on new information. Recent work in deep reinforcement learning methods has demonstrated impressive progress in such regard by developing computer programs that can solve progressively more complex tasks. Progress, though, has been delimited primarily to single task performance, and multiple days are required to become proficient in a single domain. For the present purpose, new methods that allow a single algorithm to demonstrate flexibility that more closely mirrors human-like behavior by mastering multiple and diverse sets of tasks within a significantly reduced timeframe are desirable. The overarching aim of the topic is to exceed current state-of-the-art in deep reinforcement learning by challenging existing methods to move beyond single agent-single task performance and to more closely replicate learning, memory, and navigation skills that typify human intelligence. Proof-of-concept is provided by the recent development of IMPALA (Importance Weighted Actor-Learner Architecture) that tackles one of the major impediments to progress in this realm by incorporating scalability without the concomitant sacrifice of training stability or data efficiency.1 IMPALA was evaluated on the DMLab-30 and Atari-57 challenge sets2,3 which incorporate a variety and diversity of cognitive tasks that provide useful benchmark problems for deep learning. The architecture demonstrated superior performance “in terms of data efficiency, stability, and final performance”1 as compared to A3C variants4, boasting a 49.4% versus 23.8% human normalized score on the DMLab-30 challenge set. Although IMPALA and other methods do not yet achieve human performance standards, they nonetheless provide clear evidence that implementation of artificial intelligence agents which can learn multiple domains without extensive resource requirements is conceivable. Of particular interest for the effort described herein is the development of computational architectures that enhance the ability of unmanned systems to avoid detection and interdiction during performance of military operations in potentially complex, communications-limited environments. Detection and tracking systems may utilize one or a combination of approaches that include radar systems as well as radio-frequency, electro-optical, infrared, and acoustic scanners. Interdiction systems likewise involve one or more approaches to virtually or physically intercept unmanned systems prior to mission completion and include radio-frequency and Global Navigation Satellite System jamming, spoofing to hijack communications links, lasers to destroy vital segments of the UAS airframe, nets, projectiles, and adversary drones or drone swarms.5 Unmanned systems must be capable of performing “routine” tasks (e.g., collision avoidance and object tracking) while avoiding unexpected hazards like those delineated above, thus could substantially benefit from a new architecture that confers the ability to efficiently operate in multi-task environments by performing and learning similar tasks concurrently. 

PHASE I: Leverage or create a web-based three-dimensional simulation environment that will serve as a challenge problem for training as well as a methodology for evaluating the performance of developed architectures as compared to benchmark agents. Tasks within the learning environment should reflect the diversity of tasks and goals embodied, explicitly and implicitly, in the unmanned systems mission(s) as broadly described above. They should vary visually and contain physically distinct settings to the extent that they reflect anticipated operating environments for conduct of military missions where UAS are reasonably anticipated to be used. The addition of autonomous (“bot”-like) programs that display their own unique, goal-oriented behaviors is desirable for some sub-environments. Performers will work jointly with the Government sponsor to identify environmental features and complexities that should be included. Initiate processes to develop (or extend existing) computational architectures that can resolve a collection of tasks with a single agent at a rate which is practical for purposes of scalability. Develop metrics to evaluate performance of the new architecture as compared to benchmark agents, including human performers, and to evaluate efficiency and data stability. Phase I deliverables will include (1) a final report and (2) demonstration of the training environment to the cognizant project officer. The report should also provide preliminary results on architecture performance and describe development including parameterization. The report should include plans for development of a user interface which will address Phase II expectations. Operating system, software (where applicable), and data compatibility should be specifically addressed, as should proposed location of the final interface. 

PHASE II: Phase II efforts will focus on iterative improvement to the proof-of-concept approach developed during Phase I. The performer will mature the architecture by refining the simulation environment to include, where needed and appropriate, additional and more advanced tasks and by improving architecture performance as compared to the preliminary architecture evaluated as part of the Phase I effort. The performer will identify weaknesses in performance that could be improved through additional inputs (e.g., additional sensor or coordinate data that allows more precise navigation) and will codify / relay observations to the project officer. The phase II deliverables will be a proof of concept demonstration and a report detailing (1) description of the approach, including optimization techniques and performance outcomes, (2) testing and validation methods, and (3) advantages and disadvantages / limitations of the method; the source code; and a user interface with any associated executables. 

PHASE III: In addition to implementing further improvements that would enhance use of the developed product by the sponsoring office, identify and exploit features that would be attractive for commercial or other private sector UAS applications. 

REFERENCES: 

1: Espeholt L et al. IMPALA: Scalable Distributed Deep-RL with Importance Weighted Actor-Learner Architectures. arXiv:1802.01561v3 [cs.LG], 2018.

2:  Beattie C et al. Deepmind lab. CoRR, abs/1612.03801, 2016.

3:  Bellemare MG et al. The Arcade Learning Environment: An Evaluation Platform for General Agents. Journal of Artificial Intelligence Research, 47:253–279, 2013.

4:  Mnih V et al. Asynchronous Methods for Deep Reinforcement Learning. arXiv:1602.01783v2 [cs.LG], 2016.

5:  Michel AH. Counter-Drone Systems. Center for the Study of the Drone at Bard College, http://dronecenter.bard.edu/counter-drone-systems/, 2018.

KEYWORDS: Artificial Intelligence, Simulated Environments, UAS, C-UAS, Drones 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: The objective is to produce a blockchain framework that has the capability to preserve mission-critical enterprise data during a catastrophic physical attack on the United States. 

DESCRIPTION: This project seeks to support the Department of Defense (DoD) Continuity of Operations (COOP) by developing information technology frameworks capable of preserving mission critical data despite catastrophic nuclear, electromagnetic pulse (EMP), and/or cyberwarfare attacks. [1] [2] Specifically, we plan to apply quantum-resistant blockchain technologies to protect and preserve essential mission-critical enterprise data in scenarios where a large-scale weapons of mass destruction (WMD) attack imperils the physical survival of most DoD information systems. Blockchain is a set of technologies for creating a distributed ledger of validated data blocks chained together. The creation of a block in a blockchain is a secure process, and once the addition of the data block to the blockchain is complete, the data block is both immutable and auditable. [3] There is emerging work that applies the original design principles of the Internet to producing inter-operable, robust blockchain systems that are resilient in the face of some cyber-attacks (e.g., distributed denial-of-service). [4] It is reasonable to assume that possible large nuclear and/or EMP attacks will be coupled with a cyberwarfare offensive aimed at disrupting potential defenses and neutralizing countermeasures. Quantum computing is an emerging technology that will revolutionize cyberwarfare both offensively and defensively when it appears at scale. [5] Quantum computing utilizes quantum phenomena using qubits and qubit gates. [6] By applying algorithms that exploit the special properties of qubit gates, quantum computing systems are expected to compromise many existing encryption schemes including those used in Bitcoin, a well-known blockchain system. [7] [8] Researchers have developed encryption schemes that are expected to be more resistant to quantum attacks and have begun incorporating these quantum-resistant encryption schemes into new blockchain frameworks. [9] [10] Use of quantum-resistant encryption is therefore essential in new systems that support COOP. Resilient blockchain frameworks that support COOP will need to operate in primarily two different network environments: 1) networks with medium-latency and medium-bandwidth exemplified by global Wide Area Networks (WANs), 2) networks with high-latency and low-bandwidth exemplified by WANs that include satellite links. [11] 

PHASE I: An engineering prototype will be constructed using a quantum-resistant blockchain framework designed to support COOP. The engineering prototype will be comprised from a set of twenty independent systems connected logically through the blockchain framework. The performer will conduct a series of experiments on the engineering prototype while simulating the two different network environments outlined above. In the experiments, simulated users will stochastically generate a large number of documents that are passed to one of the blockchain systems for replication to the other blockchain systems. For the simulated global WAN, these documents should vary in size from 20 kB to 10 MB. For the WAN that includes a simulated satellite link, these documents should vary in size from 20 kB to 500 kB. In addition to the network factor, the performer’s experimental design should include factors for: • degree of sudden physical compromise of the system (i.e., a percentage of systems whose total sudden physical loss is simulated), • degree of cyber-compromise (i.e., a percentage of systems whose compromise is simulated), and • degree of denial-of-service (i.e., levels of a cyber adversary’s denial-of-service efforts). The performer will observe the accuracy of the preserved documents as well as the overall recall of the generated documents at the end of each experiment. The performer will also collect the total quantity and overall characteristics of the network traffic generated by the system. The performer will verify and validate that data block generation is secure and that the generated data blocks are immutable and auditable. The phase I deliverable is a report, delivery of collected data, and a demonstration of the engineering prototype system. 

PHASE II: The performer will investigate how to integrate the resilient blockchain framework with existing DoD COOP infrastructure. An advanced prototype of the resilient blockchain framework designed for integration with existing DoD COOP infrastructure will be developed. The advanced prototype will be comprised from a set of two hundred independent systems connected logically through the blockchain framework. The advanced prototype will address any shortcomings discovered in the engineering prototype. The performer will conduct a similar set of experiments with document generation occurring at a scale ten times greater than Phase I experiments. The Phase II experiments should also include experiments where simulation of cyber-attacks and the sudden physical compromise of the system are staggered on a scale of minutes to hours. The performer will again observe the accuracy and recall of the preserved documents as well as the network traffic characteristics. The performer will verify and validate the security, immutability, and auditability of the total advanced prototype. 

PHASE III: Finalize and commercialize developed quantum-resistant blockchain frameworks for use by DoD (specifically Office of Secretary of Defense CIO and Defense Information Systems Agency) and potentially other government customers. Although additional funding may be provided through DoD sources, the awardee should look to other public or private sector funding sources for assistance with transition and commercialization. 

REFERENCES: 

1: P. M. Whitworth, "Continuity of Operations Plans: Maintaining Essential Agency Functions When Disaster Strikes," Journal of Park and Recreation Administration, vol. 24, no. 4, pp. 40-63, 2006.

2:  C. Wilson, "High altitude electromagnetic pulse (HEMP) and high power microwave (HPM) devices: Threat assessments," Library of Congress , Washington DC, 2008.

3:  S. Underwood, "Blockchain beyond bitcoin," Communications of the ACM, pp. 15-17, November 2016.

4:  T. Hardjono, A. Lipton and A. Pentland, "Towards a Design Philosophy for Interoperable Blockchain Systems," MIT, Cambridge, MA, 2018.

5:  E. B. Kania and J. K. Costello, "Quantum technologies, U.S.-China strategic competition, and future dynamics of cyber stability," in 2017 International Conference on Cyber Conflict (CyCon U.S.), 2017.

6:  A. Ramanan, "Introduction to Quantum Computing," 6 February 2018. [Online]. Available: https://blogs.msdn.microsoft.com/uk_faculty_connection/2018/02/06/introduction-to-quantum-computing/.

7:  D. Denning, "Is quantum computing a cybersecurity threat?," GCN, 20 December 2018.

8:  Emerging Technology from the arXiv, "Quantum Computers Pose Imminent Threat to Bitcoin Security," MIT Technology Review, 8 November 2017.

9:  "Post-Quantum Cryptography," NIST Computer Security Resource Center, [Online]. Available: https://csrc.nist.gov/Projects/Post-Quantum-Cryptography.

10:  J. T. Ault, "Advancing the science and impact of blockchain technology," Oak Ridge National Laboratory, Oak Ridge, TN, 2018.

11:  K. Fall, "A delay-tolerant network architecture for challenged internets," in Proceedings of the 2003 conference on Applications, technologies, architectures, and protocols for computer communications, 2003.

KEYWORDS: Blockchain, Quantum-resistant, Encryption, Continuity Of Operations, COOP, Mission-critical, Enterprise Data, Information Systems, Cyber-attack 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: DTRA seeks to investigate the feasibility of developing a standoff distance See–In-The wall (SITw) imager that can detect and positively identify hidden threats. 

DESCRIPTION: The topic is designed to identify methods producing imagery enabling detection and identification of threats hidden within concrete or similarly dense structures. Current state of the art SEE-THRU-THE-WALL (STTW) sensing capabilities mostly offer human detection and breathing signature detection, and may offer some insight into whether that person is carrying a weapon. Currently available technologies that could be further developed for our purpose include but are not limited to the following: RF (requires tradeoffs of penetration, resolution, and size of array), X-Ray backscatter (single energy offers very little discrimination in terms of material identification - explosives resemble a book), thermal imagers (material temperature gradients right behind walls are faintly distinguishable). We are interested technology breakthroughs such as multi-energy x ray backscatter, UWB imaging modality, or other novel technologies that will lead to our goal imagers. At this point, portability and Size, Weight, Power, and cost (SWaPc) are less important than the actual technology/capability, so long as it is of size and weight that could be carried into a building through a typical door. We are seeking innovative ideas and technology breakthroughs that will provide an asymmetric advantage to our warfighters by enabling them to see booby trap structures, explosives, switches, and related components. Solutions providing greater standoff distance for operators will be viewed with more favor. 

PHASE I: Identify imaging modality and show theoretical demonstration. Demonstrate pathways for meeting the performance and cost goals with the feasibility studies at the end of Phase I: Achieve feasibility for standoff and imaging. 

PHASE II: Develop the selected methodology further to develop instrumentation and validate concept with resolution and penetrability. Develop manufacturing and commercialization plans for implementing the research in production and further increase stand-off range, resolution, and size, respectively. 

PHASE III: Team up with a National Laboratory or commercial partner to develop a commercial instrument for military applications of interest to DTRA as well as domestic applications to support warfighters and regulatory inspections, border and port security, at the TRL level of 6. 

REFERENCES: 

1: Thunderstorm, Ft. Bragg, STTW Brief November 2018

KEYWORDS: See Thru The Wall, See In The Wall, Imaging, Booby Trap Structures, Hidden IED Detection 

TECHNOLOGY AREA(S): Air Platform, Chem Bio_defense, Info Systems, Ground Sea, Sensors, Electronics, Battlespace, Human Systems, Nuclear 

OBJECTIVE: To develop a radiological mapping and characterization system that extends the range of a single sensor platform by deploying and fusing data from multiple sensor platforms to enable rapid, large-area 3-D radiation detection and contamination assessment capabilities. Proposed systems must provide accurate 3-D radiation maps over large areas efficiently. Systems need to be able to detect, identify, and map gamma-ray and neutron sources over a wide range of dose rate environments. The systems must be able to determine the 3-D ground dose rate and airborne contamination for nuclear battlefield environment in real-time. The systems must provide improved battlefield situation awareness of radiation threats through 3-D spatial visualization solutions that fuse data from multiple sensor platforms, including new (such as the 3D SDF) and any deployed RADIAC systems to provide Warfighters with enhanced survey and route reconnaissance capabilities. 

DESCRIPTION: The defense community has a need to increase the effectiveness, speed, and accuracy in the mapping of radiological and nuclear materials over large areas in the context of potential structural and battlefield damage while minimizing the risks to Warfighters. 3-D mapping and data fusion technologies are required that can be deployed on a range of manned and unmanned ground and aerial vehicles to maximize the speed and accuracy in searching and mapping complex environments. Of particular interest is the deployment of small unmanned aerial platforms which avoid contamination of Warfighters and equipment and enable much faster and unhindered operation to map or search even complex environments as found after a radiological or nuclear event. 3-D mapping and radiation data fusion technologies have been demonstrated in mobile operations on single hand-portable and manned or unmanned ground and aerial vehicles illustrating the advantages over conventional means of radiation mapping. The nuclear data fused with scene data in 3-D provides not only effective means to inform emergency response and consequence management, it also provides accurate assessment of infrastructure and structural damage simultaneously. Such platforms can be envisioned to eventually deploy not only radiation detection and imaging instruments but also other sensors such as chemical, biological, and explosive sensors to provide multi-sensor, multi-modality maps. In addition, the current deployed military RADIAC systems provide Warfighters with isolated radiation measurements from one given perspective at a time. This fails to provide a fused 3-D spatial representation of threats as they appear in the scene of operation. Combining the data from multiple RADIAC kits, and new categories of sensors and fusing the data to be visualized in a 3-D space will provide the end-users with an enhanced vision of scenes in survey and route reconnaissance missions. This will enable Warfighters to better assess threats environment and provide up to the minute detailed models of the changing battlefield conditions for faster response time and lower exposure, significantly reduce the amount of interpretation and interpolation of radiological threats from multiple sources. This topic seeks innovative hardware and/or software solutions to enable the deployment of multiple 3-D radiation mapping platforms and the integration of the data to create global and large-area maps. These platforms could be any combination of ground-based and aerial vehicles equipped with radiation detection and/or imaging instruments. Of particular interest is the deployment of multiple aerial platforms as they maximize the achievable coverage in the shortest possible time. Proposed solutions must be capable of detecting and mapping gamma-ray and neutron emitting sources, providing 3-D radiation maps with better than 1-meter spatial resolution. In addition, the ability to provide maps of the concentrations of various radioisotopes with energies range from 50 keV to 3 MeV is required. Data analytics for nuclear battlefield, such as radiation contour map, dose calculations, lowest risk paths, and time versus exposure metrics, should be explored. Data products reflecting 3-D fused radiation maps need to be available for remote observation and in real-time via situational awareness tools, such as MFK/TAK. The software solution must allow for extensibility, where both new and deployed RADIAC systems can be integrated into the data stream. 

PHASE I: Develop and define the software architecture for data processing and integration, and demonstrate feasibility for the operation of multiple platforms. Create software design specifications including block diagrams and interface specifications, and integration with existing situational awareness tools, such as MFK/TAK. Perform measurements with single platform to demonstrate data fusion technologies to map and visualize radiation maps in 3-D and in real time. Utilize data from single platform and associated local maps to develop software prototype and demonstrate the feasibility to integrate data from multiple platforms resulting in integrated and global maps. Demonstrate feasibility to detect and discriminate gamma-rays and neutrons. 

PHASE II: Deliver a multi-platform system that is capable of providing global 3-D maps based on the integration of local maps from each platform and reflecting fused structural and radiation maps. At least one of the platforms is required to be an unmanned aerial system. Leverage the findings of the initial phase to implement the best data integration approach. Gamma-ray and neutron-specific global maps need to be presented on a situation awareness tools, such as MFK/TAK. More specifically, radioisotope maps need to be displayed based on the energy measurements of the gamma-rays. The system needs to be able to produce maps in nuclear battlefield environment with dose rates ranging from a few µSv/hr to >10 Sv/hr and for durations of up to 30 min covering an area of > 100,000 m2. Develop a prototype solution that demonstrates the ability to fuse multiple sensor platform data into a 3-D scene and visualize it in real time. The prototype system will be tested in a relevant environment, in order to demonstrate accurate mapping of gamma-ray and neutron emission fields from at least two platforms, one of which needs to be an unmanned aerial platform. The results will be evaluated to determine the ability of the proposed solution to satisfy requirements for military use in the field. During this phase, DoD end-user group(s) will be identified to begin engagement with. Discussions with the end -users will inform the transition plan for Phase III. 

PHASE III: Following a successful Phase II development and demonstration, Phase III will further improve system design, visualization capability, engineering, ruggedization, scalability, manufacturability, and maturation to meet DTRA and end-user requirements, including the development of a plan to enable successful technology transition at the end of this phase. Develop commercial system to integrate multiple systems providing 3-D mapping and visualization capabilities for wide range of applications, enhancing the tool set of Warfighters while minimizing the exposure to risks. 

REFERENCES: 

1: G. Knoll, Radiation Detection and Measurement. John Wiley & Sons, 2010.

2:  K. Vetter, R. Barnowski, R. Cooper, T. Joshi, A. Haefner, B. Quiter, R. Pavlovsky, "Gamma-Ray Imaging for Nuclear Security and Safety: Towards 3D Gamma-Ray Vision", Nucl. Instr. Meth. A. 878 (2018) 159.

3:  A. Haefner, R. Barnowski, M. Amman, J. Lee, P. Luke, L. Mihailescu, K. Vetter, "Handheld Real-time Volumetric 3-D Gamma-ray imaging", Nucl. Instr. Meth. Nucl. Instr. Meth. A. 857 (2017) 42.

4:  K. Vetter, A. Haefner, R. Barnowski, R. Pavlovsky, T. Torii, Y. Sanada, Y. Shikaze, "Advanced Concepts in Multi-Dimensional Radiation Detection and Imaging", Japan Physical Society Conference Proceedings JPS Conf. Proc 11 (2016) 070000-1.

5:  R. Barnowski, A. Haefner, L. Mihailescu, K. Vetter, "Scene Data Fusion: Enabling Real-Time Volumetric Gamma-Ray Imaging", Nucl. Instr. Meth. A. 800 (2015) 65.

6:  R. Pavlovsky, A. Haefner, T.H. Joshi, V. Negut, K. McManus, E. Suzuki, R. Barnowski, K. Vetter, "3-D Radiation Mapping in Real-Time with the Localization and Mapping Platform LAMP from Unmanned Aerial Systems and Man-Portable Configurations", To be submitted to Nucl. Instr. Meth. A.

KEYWORDS: Radiation Detection, Data Fusion, 3-D Mapping, Real-time, Multi-platform Systems, Neutron/gamma Radiation Detection And Mapping 

TECHNOLOGY AREA(S): Materials, Sensors, Battlespace, Nuclear 

OBJECTIVE: Develop a rugged alpha/beta detector that does not possess a fragile window common to alpha/beta detectors on the market today. This will enable both military and commercial users with a more durable instrument without the service interruptions due to punctures to the window. 

DESCRIPTION: Radiation detection media is typically housed behind rugged packaging which protects it from the elements and allows the packaging to be cleaned to prevent unintended source identification. Due to the short range of alpha/beta particles in matter, detectors for the identification of these particles must be packaged behind a thin window, usually aluminized Mylar. However, this provides a structural weakness that is easily punctured or damaged in field conditions. This impacts logistics, cost, and operational efficiency. DTRA seeks an alternative that would allow for use without risk of damage to a window. This capability would provide value in non-military environments such as factories or industrial areas where radioactive materials may be present. This capability should allow for field use, with minimal or no consumables, and sensitivity to low-energy alpha and beta particles (<1 MeV). The device should be easily hand portable. 

PHASE I: Develop, evaluate, and validate innovative techniques, concepts, and/or a breadbroad prototype for use in an alpha/beta detector without a thin window. By the end of phase one, techniques, concepts, and/or a breadboard prototype should have been demonstrated to have the potential for fulfilling a fully integrated prototype. 

PHASE II: Develop a prototype and demonstrate its ability to meet the requirements provided in the description. An assessment regarding the performance and the ability to perform in field conditions will be performed. This phase will utilize the materials and techniques developed in Phase I of this research. Develop manufacturing and commercialization plans for implementing the research into production and then into the marketplace. 

PHASE III: In addition to applications of interest to DTRA, the alpha/beta detector without a thin window will have applications in industry and power generation. 

REFERENCES: 

1: G. Knoll, Radiation Detection and Measurement. John Wiley & Sons (2010)

2:  S.H. Hwang, J.M. Lee, K.B. Lee, T.S.Park, "Development of a windowless multi-wire proportional chamber (MWPC) counting system for measuring extended-area beta source," Applied Radiation and Isotopes, Volume 126, Pages 175-178 (2017)

3:  Ü. Ören, J. Nilsson, L. Herrnsdorf, C.L. Rääf, S. Mattsson, "Silicon diode as an alpha particle detector and spectrometer for direct field measurements," Radiation Protection Dosimetry, Volume 170, Issue 1-4, Pages 247–251 (2016)

KEYWORDS: Alpha Detection, Beta Detection, Contamination Monitoring 

TECHNOLOGY AREA(S): Air Platform, Sensors, Electronics, Space Platforms 

OBJECTIVE: To develop an automated software algorithm that can provide accurate temporal deformation characterization of a surface or target in the presence of three-dimensional relative camera motion 

DESCRIPTION: DOD, DOE, and their contractors have an interest in dynamic digital photogrammetry as a remote sensing capability, particularly in environments where the ability to deploy sensitive ground sensors may be limited or there is a need to gather data over large areas. This can have applications for a variety of purposes such as change detection, battle damage assessment, explosive phenomenology, and post-test analysis of structural and weapon tests. The DTRA RD-TS Test Science and Technology Department has been working on the development of capabilities for performing dynamic digital photogrammetry using digital image correlation (DIC) from aerial platforms. Dynamic digital photogrammetry differs from the more common static photogrammetry (4,5,6) that uses only photos before and after an event to describe the total change. An example of an aerial platform would be two unmanned aerial systems (UAS) carrying high-speed cameras. DTRA RD-TS took advantage of recent developments in commercial off-the-shelf (COTS) DIC solutions to develop a capability that could provide an accurate temporal record of displacement at any point in the field-of-view during a dynamic event such as a buried explosion that creates ground deformation at the surface. The DIC estimates of ground deformation at the surface can then be compared to ground truth sensor information to evaluate their accuracy. However during the process of developing this capability, RD-TS experienced some challenges in small field of view characterization of small seismic sources (such as a sledgehammer or accelerated weight drop as viewed from ground-mounted cameras) and large field of view characterizations (20m x 20m or greater fields of view) of larger seismic sources from aerial platforms. One of the primary challenges was that many of the commercial software platforms for performing DIC, such as GOM Correlate Professional (2), which was used for initial RD-TS investigations, requires a pre-test calibration procedure to accurately characterize the lens parameters and camera positioning. This works well in a laboratory environment where there is no relative camera motion, but in field conditions there can be camera jitter from wind or small movements due to UAS position corrections that need to be accounted for (14,17,18). In this case, the DIC displacement errors increase as a function of time and also vary spatially over the field of view as the cameras move away from their initial calibrated position. Correction methods could include: multiple recalibrations over a shorter time period than the average timescale of significant relative motion when the calibration targets remain in the field of view; make adjustments to the images based on assumptions of non-moving points in the field of view prior to DIC analysis; or record the actual relative motion and make corrections to the DIC results or calibration files based on the known relative motion. With the technique RD-TS used to perform large field of view calibration with TRITOP and DIC analysis with GOM Correlate Professional (2), coded targets can be removed after calibration if no camera motion is expected. If only absolute motion is anticipated (e.g., cameras are connected by a camera bar) and there are motionless points in the field of view, results can be corrected using rigid body motion compensation. The purpose of this SBIR topic is to address the situation when there is relative camera motion, there may not be motionless points in the field of view, calibration targets or photomarkers may not be desirable in the field of view, and the surface of interest may be not be an ideal high-contrast speckled pattern (such as rock or geological surfaces)(11). In hostile territories, it also might not be possible to perform a pre-test calibration and a pre-calibrated camera/lens pair and motionless points in the field of view may be required (such as is required for the static photogrammetry software ShapeMetrix(5)). An automated software algorithm is required that can handle relative camera motion and can use known distances between easily identifiable features in the field of view for georeferencing. 

PHASE I: During Phase I, an initial approach will be developed for designing an automated software algorithm that can be utilized with fields of view ranging from less than one square meter up to very large fields of view covering 10s to 100s of square meters. The algorithm needs to either be insensitive to relative motion or able to correct for it. This could involve adapting an existing commercial software (2,3), developing a new software algorithm (potentially starting from an open source DIC code (7)), or automating a static photogrammetry software (4,5,6) such as ShapeMetrix to work for dynamic photogrammetry. The algorithm needs to be bench tested with a simple dynamic scenario and two low-cost, high-resolution and reasonably high-speed cameras (minimum of 60 frames/sec although higher is preferred (19)). There needs to be a comparison of results when the cameras are motionless to results with relative camera motion. No aerial platform is necessarily required; the cameras can be moved by hand. 

PHASE II: During Phase II, the digital image correlation software algorithm will be refined, documented, and will be tested in more realistic conditions. This will require one small-scale test using a small seismic source (such as a sledgehammer) with some method of obtaining ground truth. A second test needs to be performed using a larger field of view of at least 20m x 20m and a moving source with the same ground truth requirement. A fully successful Phase II would also allow for integration of cameras onto a wide range of aerial platforms ranging from UAS to satellites. 

PHASE III: DUAL USE APPLICATIONS: In addition to defense applications, this method has broad academic applications (1,8,9,10) such as environmental change monitoring (10) , monitoring hazards such as landslides (16), or civil applications (9,15). 

REFERENCES: 

1: Colomina, I. and P. Molina (2014), Unmanned aerial systems for photogrammetry and remote sensing: A review, ISPRS Journal of Photogrammetry and Remote Sensing, 92, pp 79 – 97

2:  Website: GOM Correlate, https://www.gom.com/3d-software/gom-correlate.html

3:  Website: Xcitex – ProAnalyst Motion Analysis Software, https://www.xcitex.com/proanalyst-motion-analysis-software.php

4:  Website: Pix4d: Professional photogrammetry and drone-mapping, https://www.pix4d.com/

5:  Website: ShapeMetrix 3d, https://3gsn.at/produkte/shape-metrix/

6:  Website: ADAM Technology, 3DM Analyst, https://www.adamtech.com.au/3dm/Analyst.html

7:  Website: DICe Digital Image Correlation engine, Sandia National Laboratories, https://dice.sandia.gov (Open Source)

8:  Vander Jagt, B., A. Lucieer, L. Wallace, D. Turner, and M. Durand (2015), Snow Depth Retrieval with UAS Using Photogrammetric Techniques, Geosciences, 5, 264-285

9:  doi:10.3390d., /geosciences5030264

10:  Reagan, D., A. Sabato, C. Niezrecki (2017), Unmanned aerial vehicle acquisition of three-dimensional digital image correlation measurements for structural health monitoring of bridges. In SPIE Smart Structures and Materials+ Nondestructive Evaluation and Health Monitoring, 1016909

11:  Ferreira, E., J. Chandler, R. Wackrow, and K. Shiono (2017), Automated extraction of free surface topography using SfM-MVS photogrammetry, Flow Measurement and Instrumentation, 54, 243-249

12:  Yu, J.H. and P.G. Dehmer (2012), Digital Image Correlation of Dynamic Impact Deformation Without Painted Dots Using ProAnalyst 3-D Photogrammetry Software, Army Research Laboratory ARL-TR-5913

13:  Kedzierski, M. and P. Delis (2016), Fast Orientation of Video Images of Buildings Acquired from a UAV without Spabilization, Sensors, 16, 951

14:  doi:10.3390/s16070951

15:  Habib, A., I. Detchev, and E. Kwak (2014), Stability Analysis for a Multi-Camera Photogrammetric System, Sensors, 14, 15084-15112

16:  doi:10.3390/s1408115084

17:  Reich, M., J. Unger, F. Rottensteiner, and C. Heipke (2014), A new approach for an incremental orientation of micro-UAV image sequences

18:  Unger, J., M. Reich, and C. Heipke (2014), UAV-based photogrammetry: monitoring of a building zone, The International Archives of Photogrammetry, Remote Sensing and Spatial Information Sciences, Volume XL-5, ISPRS Technical Commission V Symposium, 23-25 June 2014, Riva del Garda Italy

19:  Gomez, C. and H. Purdie (2016), UAV-based Photogrammetry and Geocomputing for Hazards and Disaster Risk Monitoring – A Review, Geoenvironmental Disasters, 3:23, doi: 10.1186/s40677-016-0060-y

20:  Yang, Y., Z. Lin and F. Liu (2016), Stable Imaging and Accuracy Issues of Low-Altitude Unmanned Aerial Vehicle Photogrammetry Systems, Remote Sensing, 8, 316

21:  doi: 10.3390/rs8040316

22:  Miller, T.J., H.W. Schreier, and P. Reu (2007), High-speed DIC Analysis from a Shaking Camera System, in Society for Experimental Mechanics, 2007

23:  Springfield, MA

24:  Reu, P.L (2011), High/Ultra-high speed imaging as a diagnostic tool, Sandia National Laboratory, SAND2011-0978C

KEYWORDS: Remote Sensing, Photogrammetry, Digital Image Correlation 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop innovative methods for propelling missiles out of a Vertical Launch System (VLS) without using the first stage rocket. 

DESCRIPTION: This topic seeks design concepts for propelling missiles weighing up to 10,000 lb out of a VLS canister to a distance of 100+ ft without using the first stage rocket. Successful proposals should stay within the constraints of the VLS launcher and the footprint of current host platforms. An alternate method for ejecting the missile out of the launcher could potentially increase the missile performance to meet future needs. 

PHASE I: Develop a proof of concept. Identify designs and conduct a feasibility assessment for the proposed solution. Perform analysis to demonstrate the concept and to provide an understanding of the new and innovative technology. 

PHASE II: Develop and refine the proposed solution based on the results and findings of Phase I. Validate the feasibility of the Phase I concept by development and demonstrations through testing to ensure performance objectives. Validations would include, but not be limited to, system simulations, operation in test-beds, or operation in a demonstration subsystem. The Phase II effort should result in a prototype with substantial commercialization potential. 

PHASE III: Based on Phase II lessons learned, revise the systems model to prove out the new design. Develop and execute a Phase III incremental test & integration plan that will produce a final prototype. Demonstrate interface capability with a government furnished VLS. 

REFERENCES: 

1: https://www.dsiac.org/resources/journals/dsiac/fall-2014-volume-1-number-2/promising-future-us-navy-vertical-launching

2:  https://www.raytheon.com/capabilities/products

3:  http://www.seaforces.org/wpnsys/SURFACE/Mk-41-missile-launcher.htm

4:  https://www.baesystems.com/en-us/product/vertical-launching-system-vls-mk41

5:  https://www.navy.mil/navydata/fact_display.asp?cid=2100&tid=550&ct=2

KEYWORDS: Vertical Launching System, VLS, Mk 41 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop an optimized Dynamic Object Oriented Requirements System (Doors) Database Tool. 

DESCRIPTION: This topic seeks to develop a DOORS Database tool that will optimize the Computer Program Change Requests (CPCRs) and missile defense Test Incident Reports (TIRs) list by component software area. Maximize CPCR & TIR implementation at the lowest system impact, cost, and schedule to include Software Lines of Code (SLOC) count. Currently there is not a unified method to analyze CPCRs and TIRs for applicability to group work packages. The impact (cost, baseline control, and ship implementation) of opening up a software code package (specific to the hardware where the software resides) for insertion of new and repair code fixes precludes frequent implementation; usually once a year at most. Due to the complex nature of the weapon system code, manual sorting and evaluation frequently misses opportunities to insert CPCR and TIR fixes. An automated process is needed to avoid missing code fixes. 

PHASE I: Develop a proof of concept design. Identify designs and conduct a feasibility assessment for the proposed solution. Perform analysis to demonstrate the concept and to provide an understanding of the new and innovative technology. 

PHASE II: Develop and refine the proposed solution based on the results and findings of Phase I. Validate the feasibility of the Phase I concept by development and demonstrations that will be tested to ensure performance objectives are met. Validation would include, but not be limited to, system simulations, operation in test-beds, or operation in a demonstration subsystem. The Phase II effort should result in a prototype with substantial commercialization potential. 

PHASE III: Based on Phase II lessons learned, revise the systems model to prove out the new design. Develop and execute a Phase III incremental test and integration plan that will produce a final prototype. 

REFERENCES: 

1: https://www.ibm.com/support/knowledgecenter/en/SSYQBZ_9.6.1/com.ibm.doors.requirements.doc/topics/c_welcome.html

2:  http://lbne2-docdb.fnal.gov/cgi-bin/RetrieveFile?docid=3472&filename=doors_getting_started.pdf&version=18

3: 

KEYWORDS: DOORS Database, Optimization Tool 

TECHNOLOGY AREA(S): Sensors 

OBJECTIVE: Develop a low probability of detection illuminator for missile defense ship applications. 

DESCRIPTION: Ship Illuminators have a large RCS. The development of an innovative solution that would allow the Illuminator to operate in its spectrum but absorb other radio frequency spectrums would result in a lower overall RCS without impacting Illuminator performance. Increasing survivability and mission effectiveness by reducing detectability has become very important. The use of radar absorbing materials or alternate solutions to reduce the RCS can provide for an increase in mission effectiveness while reducing detectability of the ships. 

PHASE I: Develop a proof of concept design; identify materials and designs and conduct feasibility assessment for the proposed solution. Perform analysis and limited bench level testing to demonstrate the concept and to provide an understanding of the new and innovative technology. 

PHASE II: Based on the results and findings of Phase I, develop and refine the proposed solution. Validate the feasibility of the Phase I concept by development and demonstrations that will be tested to ensure performance objectives are met. Validation would include, but not be limited to, system simulations, operation in test-beds, or operation in a demonstration subsystem. The Phase II effort should result in a prototype with substantial commercialization potential. 

PHASE III: Based on Phase II lessons learned, revise methods/material selection and prove out the solution. Develop and execute a Phase III incremental test and deployment plan. 

REFERENCES: 

1: https://www.researchgate.net/publication/305721036_Radar_Cross_Section_Reductiondd

2:  https://www.gd-ots.com/armaments/naval-platforms-system/aegis-illuminator/

3:  https://www.globalsecurity.org/military/systems/ship/systems/an-spg-62.htm

KEYWORDS: Radar Cross Section Reduction 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Develop an innovative HTM algorithm to pre-process raw radar return data. 

DESCRIPTION: This topic seeks to develop innovative applications of the open source HTM algorithm to pre-process raw radar returns in order to reduce debris, clutter, and other unwanted return data which should lead to reduced radar loading and an increase in engagement capability. By pre-processing the returns, erroneous signals would not be forwarded to the computer suite for processing. This should allow the weapon system to process additional targets since it is not spending as much time processing clutter data. 

PHASE I: Develop a proof of concept design. Identify designs and conduct feasibility assessment for the proposed solution. Perform an analysis to demonstrate the concept and an understanding of the new and innovative technology. 

PHASE II: Develop and refine the proposed solution based on the results and findings of the Phase I. Validate the feasibility of the Phase I concept by development and demonstrations that will be tested to ensure performance objectives are met. Validation would include, but not be limited to, system simulations, operation in test-beds, or operation in a demonstration subsystem. The Phase II effort should result in a prototype with substantial commercialization potential. 

PHASE III: Based on Phase II lessons learned, revise the systems model to prove out the new design. Develop and execute a Phase III incremental test & integration plan that will produce a final prototype. 

REFERENCES: 

1: https://numenta.com/machine-intelligence-technology/

2:  https://numenta.org/resources/HTM_CorticalLearningAlgorithms.pdf

KEYWORDS: Hierarchical Temporal Memory, Algorithm, Radar Returns, Radar Loading 

TECHNOLOGY AREA(S): Info Systems, Battlespace 

OBJECTIVE: Develop innovative techniques for BM extension into IAMD. 

DESCRIPTION: This topic seeks innovative BM techniques to provide robustness and flexibility for managing future IAMD threats. As the battle management paradigm, scope, and threats increase there is a need for greater coordination, intelligent control, and flexibility. IAMD presents new opportunities for dynamically engaging missile threats in the presence of air defense forces, balancing the need to strike fast with the requirement to protect, and leverage lower tier blue forces. Consequence management will be important to consider as shoot opportunities become available – ensuring the warfighter knows the risks as well as necessity for striking at a given time. Managing sensors and weapons across tiers, maintaining battle control, and providing optimal handover to weapon systems is essential. Battle management can be pre-scripted for well understood engagements, but complex scenes will require a more comprehensive analysis. The current system informs commanders across combatant commands about threats potentially crossing multiple command areas, and about sensors and weapons in multiple command areas. Moving to the next generation air and missile defense, this structure becomes yet more complex adding a horizontal layer under partitioned command areas. The ability to close the fire control loop with off board sensors is a critical challenge. Novel techniques developed under this task should accommodate multiple areas of air defense operation. Specific areas of interest include techniques to determine when a scripted plan is adequate for the engagement, based on the developing battle, and that can also dynamically adapt when needed. Priorities for sensor tasking and timelines for weapon cueing should be defined as well as other critical information that supports warfighter actions. 

PHASE I: Develop and demonstrate a methodology for IAMD that accommodates multiple sensors, tiers, and Areas of Responsibility (AORs) to address advancing threats. The basic architecture should be modular in design to facilitate maintenance, upgrades, and scalability for future sensors and defensive capabilities. 

PHASE II: Refine and update concept(s) based on Phase I results, and demonstrate the impacts of raid scenarios on stressing tasking environments. Demonstrate the Battle Management scheme can accommodate multiple launches and maintain track while transiting various Combatant Commander AORs. If desired by the developer, the government may choose to provide a government testbed at no cost if the developer wishes to utilize the facility for high fidelity testing. 

PHASE III: Demonstrate the new technologies via operation as part of a complete system or operation in a system-level test bed to allow for testing and evaluation in realistic scenarios. Market technologies developed under this topic to relevant missile defense elements directly, or transition them through vendors. 

REFERENCES: 

1: www.dote.osd.mil/pub/reports/FY2016/pdf/army/2016iamd.pdf

2:  https://ndiastorage.blob.core.usgovcloudapi.net/ndia/2013/IAMD/Ray.pdf

3:  https://ndiastorage.blob.core.usgovcloudapi.net/ndia/2014/IAMD/Kilby.pdf

4:  www.jcs.mil/Portals/36/Documents/Publications/JointIAMDVision2020.pdf

KEYWORDS: Integrated Air And Missile Defense, Missile Defense System, Battle Management 

TECHNOLOGY AREA(S): Info Systems, Electronics, Weapons 

OBJECTIVE: Develop innovative BMHy system security methods for current embedded systems to protect Critical Program Information (CPI). 

DESCRIPTION: This topic seeks to design and develop a BMHy that integrates multiple security disciplines and approvals. A Hypervisor is a computer program that manages and runs one or more guest virtual machines that share host hardware or processing platform resources. Hypervisors may emulate hardware resources for their guest(s) and/or allow guest(s) to access the host’s hardware resources. While there are current hypervisors for National Security Administration (NSA) red/black separation and cross-domain solutions, there are no hypervisors that support real-time embedded systems on Department of Defense (DoD) hardware and also add additional protection of CPI within guests. By developing and integrating security disciplines into a BMHy, this should robustly protect CPI in guests from reverse engineering and cyber-attacks and secure control over software execution by integrating with hardware resources. Because this topic is seeking a BMHy to protect CPI, the BMHy itself should uphold its own secure execution of the function against Hypervisor-vulnerabilities. 

PHASE I: Research and develop methodologies for proof-of concept on a representative system that has multiple protections over known vulnerabilities. The purpose should be to demonstrate the feasibility, uniqueness, and robustness of the protection that the proposed technology will offer. Estimate the performance impact. A partnership with a current or potential supplier of missile defense applications, and/or state-of-the-art commercial vendor is highly desirable. 

PHASE II: Develop, demonstrate, and validate a prototype of the developed methodologies or techniques on a representative weapon processing platform. Analysis should be conducted to evaluate the ability of the technology protection in a real-world situation. Identify any anticipated commercial benefit or application opportunities of the innovation. A partnership with a current or potential supplier of missile defense applications, and/or state-of-the-art commercial vendor is highly desirable. 

PHASE III: Integrate the developed technology into a critical system application, for a missile defense system level test-bed. Demonstrate the application to one or more element systems, subsystems, or components as well as the product’s utility against industrial espionage. Perform an analysis to evaluate the performance of the technology in a real-world situation. Establish a partnership with a current or potential supplier of missile defense applications, or a commercial vendor. 

REFERENCES: 

1: https://en.wikipedia.org/wiki/Hypervisor

2:  https://nvlpubs.nist.gov/nistpubs/SpecialPublications/NIST.SP.800-125Ar1.pdf

3:  http://dx.doi.org/10.6028/NIST.SP.800-125B

4:  https://www.niap-ccevs.org/MMO/PP/pp_base_virtualization_v1.0.pdf

5:  https://at.dod.mil/content/department-defense-policy

KEYWORDS: Bare-metal Hypervisor, Critical Program Information, Protection, Security, Reverse Engineering, Cybersecurity 

TECHNOLOGY AREA(S): Materials, Electronics 

OBJECTIVE: Develop a Supercapacitor using bicarbon-based materials derived from plant cellulose. 

DESCRIPTION: This topic seeks to address a manufacturing technology objective to provide an environmentally friendly alternative to common precious metals and chemicals currently used in supercapacitors by demonstrating the supercapacitive properties of bio-carbon materials derived from plant cellulose. Supercapacitor devices are charged to exhibit high power densities and long lifetimes. These properties allow supercapacitors to bridge the gap in performance between batteries and fuel cells. Some supercapacitors utilize precious metals and/or toxic chemicals to achieve top performance. An in-depth understanding of the nanostructure over multiple length scales is paramount to optimize performance and to design better devices. 

PHASE I: Identify candidate materials derived from plant cellulose and predict/characterize their capacitance properties in order to optimize their supercapacitor properties. Verify stable capacitance of a proof-of-concept bicarbon based environmentally friendly supercapacitor that can meet a minimum 100 Farad capacitance with an objective 500 Farads for 10,000 recharge cycles with operating voltages between 2 and 4 Volts. 

PHASE II: Develop prototype supercapacitor(s) that can demonstrate the Phase I capacitance design parameters. Characterize the cellulose nano-architecture performance and the stability of the materials across a typical military system life time of 10-20 years by utilizing accelerated life testing methods. 

PHASE III: Establish a partnership with a current or potential supplier of missile defense applications, or a commercial vendor. Integrate the developed technology into a missile defense or commercial application. Evaluate the performance of the technology in a real-world situation. 

REFERENCES: 

1: Sustainable Energy Fuels, Royal Society of Chemistry, University College London, London. https://physicsworld.com/a/supercapacitor-nano-architecture-designing-a-plant-powered-future/

2:  IEEE transactions on sustainable energy: October 2012. https://ieeexplore.ieee.org/document/6317213

KEYWORDS: Supercapacitor; Biotechnology; Materials; Plant Cellulose; Capacitor; Bicarbon; Nanotechnology 

TECHNOLOGY AREA(S): Info Systems, Materials, Weapons 

OBJECTIVE: Develop an innovative methodology that will enable hydro-code tools (e.g. Dyna, Paradyn, Zapotec, Velodyne, etc.) that model C-C materials at high temperature with high-rate loadings, to be used as a predictive tool for analysis of energetic events like high-velocity impacts or explosive loadings. 

DESCRIPTION: This topic seeks innovative methodologies that estimate C-C modeling uncertainties in hydro-code results in a predictive tool that does not depend on being able to interpolate between known test results. Due to limitations of test venues available for system-level tests that can only partly cover the range of operational conditions for aerospace systems, high costs, and challenging data collection, the ability of hydro-codes to simulate load cases of interest exceeds the capability of test venues to perform high-fidelity experiments. Thus, uncertainty quantification methodologies for hydro-codes and C-C materials is of interest as they would serve as a bridge for uncertainty comparisons between test data, hydro-code tools, and engineering tools. In order to perform meaningful hydro-code analysis for cases outside the parameter space of interpolation between test data points, uncertainty quantification is critical. When extrapolating beyond known benchmarking tests, uncertainty quantification makes the difference between a tool that can assess trends, and a tool that can be predictive. The typical approach for reconciling computational models with test data is to use tunable parameters in the system model to give the best agreement with the measured test response of the system. It may be possible to look at a variety of test responses, and tune model parameters for the best over-all fit to multiple sets of data. Goodness-of-fit parameters in the statistics can be used to estimate the uncertainty. Some uncertainty will be due to assumptions and approximations in the code itself, some will be due to assumptions in construction of the model, and some will be due to input parameters like material properties. For this topic, the uncertainty in material property test data for C-C due to manufacturing process variability should be characterized in terms of the material response. For meaningful comparisons with data, the measurement uncertainty must be quantified as well, and meaningful metrics must be chosen for fracture and failure of the C-C material and the overall structure. In the case of C-C materials, the variability in manufacturing processes is a key driver of the variability in material properties. Thus, the proposed methodology should address both the C-C and hydro-code model uncertainties as well as the uncertainty present in the input parameters (uncertainties in the measurements of material properties). Load cases of interest will be for high-strain-rate and high-temperature loadings of structural systems.  

PHASE I: Formulate an innovative methodology for uncertainty quantification of hydro-code predictions using C-C models that are based on material characteristics from uncertain test data. Include the effects of manufacturing process variability, such as phase transformations, cloth wrap types, weave changes, shrinkage, and residual stresses. Characterize test data in terms of material response. Demonstrate feasibility using a representative structural model with high strain-rate loadings (e.g. high-velocity impact or explosive loading that would cause strain-rates of 10^7 sec^-1 and above over a range of temperatures from 25 degrees C up to well above 1,000 degrees C. Consider relevant cases where experimental data sets are available. 

PHASE II: Perform further demonstration of the Phase I methodology with more complex, larger-scale models of interest to the government, and use of a broader range of experimental data sets. Include additional sources of uncertainty and show the relative importance of the various error sources for full-scale testing, such as flight test, sled test, or arena test. Demonstrate an interface with missile defense application engineering level tools, and hydro-codes. 

PHASE III: Transition the uncertainty quantification capability for first-principle physics-based modeling capability developed under this program to target lethality and debris prediction efforts. Fully integrate the uncertainty quantification tool with an appropriate hydro-code and execute model runs for design and analysis cases of interest to the government. 

REFERENCES: 

1: Roy and Oberkampf, "A comprehensive framework for verification, validation and uncertainty quantification in scientific computing," Comput. Methods Appl. Mech. Engrg. 200 (2011) 2131-2144

2:  Dimitrienko, "Modeling of carbon-carbon composite manufacturing processes," Composites Part A: Applied Science and Manufacturing, Vol. 30, No. 3, 221-230, 1999.

3:  Center for Applied Scientific Computing, "The PSUADE Uncertainty Quantification Project," Lawrence Livermore National Laboratory, US Department of Energy, https://computation.llnl.gov/casc/uncertainty_quantification

4:  "DAKOTA – Explore and predict with Confidence," National Technology and Engineering solutions of Sandia, LLC, Sandia National Laboratories, US Department of Energy, https://dakota.sandia.gov

5:  http://www.mda.mil/news/downloadable_resources.html

6:  Zucas, J.A., "Introduction to hydrocodes (Studies in Applied Mechanics)," Elsevier, New York, NY, 2004.

7:  McGlaun, J.M., Tompson, S.L., Elrick, M.G., "CTH: A three-dimensional shock wave physics code," International Journal of Impact Engineering, Vol. 10, Issue 1, 1990, 351-360.

8:  Melis, et al., "Reinforced Carbon-Carbon Subcomponent Flat Plate Impact Testing for Space Shuttle Orbiter Return to Flight," NASA/TM 2007-214384, September 2007.

9:  Carney, et al., "A Heterogeneous Constitutive Model for Reinforced Carbon-Carbon using LS-DYNA, 10th International LS-DYNA User’s Conference – Material Modeling, 2008.

KEYWORDS: Uncertainty Quantification, Hydro-codes, Hydro-structural Codes, Carbon-Carbon Composites, High-strain-rate Material Properties, High-temperature Material Properties 

TECHNOLOGY AREA(S): Info Systems 

OBJECTIVE: Automate fixes for cyber vulnerabilities in source code based on results from commercially available scanning software. 

DESCRIPTION: This topic seeks innovative modern methods or technologies that alleviate the burden associated with fixing cyber vulnerabilities in already developed source code. This topic does not seek to identify the vulnerabilities as there are many commercial-off-the-shelf tools that perform this function. A listing of such tools is included in the references. The idea is that once scanning software has identified vulnerabilities in source code through some sort of report, innovative algorithms based on machine learning or artificial intelligence methodologies can take those results and automate code fixes. Proper documentation and traceability is critical to this process as developers will need to understand what and how a cyber-vulnerability is being fixed in the source code base. Cyber hardening code is a top priority of the Department of Defense (DoD) and such a tool would save millions of dollars benefiting not only the DoD industry but many commercial entities as well. There are many categories associated with cyber vulnerabilities that will need to be addressed and each category comes with its own unique challenges in how to address them. Major categories that will need to be covered are: Buffer Overflows, Injection Vulnerabilities, Sensitive Data Exposure, Broken Authentication and Security Misconfiguration just to name a few. Different types of source code will also need to be addressed (i.e. C, C++, Java, Python, etc.) as well as a discussion on how different compilers may affect the end result. 

PHASE I: Design and develop improved solutions, methods, and concepts for automating cyber vulnerabilities fixes in source code. The solutions should capture the key areas where new development is needed, suggest appropriate existing methods and technologies, and incorporate new technologies researched during design development. Define the architecture and validity across multiple cyber vulnerabilities with analysis across different types of source code file structures. 

PHASE II: Complete a detailed prototype design incorporating government performance requirements. Coordinate with the government during prototype design and development to ensure that the delivered products will be relevant to ongoing and planned missile defense projects. 

PHASE III: Scale-up the capability from the prototype utilizing the software technologies developed in Phase II into a mature, full-scale, field-able capability. Work with missile defense integrators to transition the technology into existing missile defense modeling and simulation programs. 

REFERENCES: 

1: November 6, 2018. "Top 40 Static Code Analysis Tools". Retrieved from https://www.softwaretestinghelp.com/tools/top-40-static-code-analysis-tools/

2:  April 26, 2018. "DeepCode cleans your code with the power of AI". Retrieved from https://techcrunch.com/2018/04/26/deepcode-cleans-your-code-with-the-power-of-ai/

3:  October 10, 2017. "Practical Integer Overflow Prevention". Retrieved from https://pdfs.semanticscholar.org/074b/8dd5bf9be49534d28ea1be8dc96aa1652cc3.pdf

KEYWORDS: Cybersecurity, Machine Learning, Self-Coding 

TECHNOLOGY AREA(S): Materialssensors, Electronics 

OBJECTIVE: Identify and mature technologies for electro-optical and infrared (EO/IR) and radio frequency (RF) seeker/sensors for high Mach, endo-atmospheric flight. 

DESCRIPTION: This topic seeks to develop technologies to enable a forward-looking seeker/sensor that operates in a high Mach, endo-atmospheric flight regime. The aerothermal environment for a hypersonic interceptor is very severe at the interceptor's nose tip. The seeker/sensor concept should survive high heating rates (>250 W/cm^2), high pressures, flow-field density changes, distortion, and look through shock waves. Enabling solutions may include: high temperature, transparent materials, distributed apertures, cooling methods, fast-steering mirrors, shock mitigation, thermal management devices, phase change materials, etc. In the response, proposers should describe the forward-looking seeker concept and identify how the proposed technology enables a forward-looking seeker/sensor. Proposers should estimate size, weight, and power (where applicable). 

PHASE I: Conduct a design study that shows the feasibility of the concept, backed with low-fidelity, proof-of-concept testing. Provide estimated performance and reliability characteristics. Demonstrate an understanding of the seeker/sensor design and the fundamentals of the technology enhancement proposed. 

PHASE II: Continue development through detailed design and analysis followed by fabrication of prototype hardware and developmental testing to anchor modeling results. The proposer should consider appropriate environmental testing, such as temperature variation, random vibration, flight shock, etc. Update the design based on test results. Provide performance and reliability characteristics, as well as a manufacturing approach and estimated costs. 

PHASE III: Work with missile defense integrators to transition the technology into existing missile defense programs. Dual use applications of specialized technologies include commercial aero-optics and thermal management of electronics. 

REFERENCES: 

1: Pue, Alan J. "Missile Concept Optimization for Ballistic Missile Defense." JOHNS HOPKINS APL TECHNICAL DIGEST, VOLUME 32, NUMBER 5, pp. 774 – 786. 2014. www.jhuapl.edu/techdigest.

2:  Cantrell, M., VanHorn, T., Muras, A. "AIAA 92-1215 – Endoatmospheric LEAP. 1992 Aerospace Design Conference.

KEYWORDS: EO/IR, Infrared, Transparent Materials, Seeker, Sensor, Thermal Management, Mirrors, Apertures, Aero-optics 

TECHNOLOGY AREA(S): Sensors, Electronics, Space Platforms 

OBJECTIVE: Develop a low Size Weight and Power (SWaP) and space-qualifiable computer-hardware solution for next generation machine vision applications. 

DESCRIPTION: This topic seeks innovative reprogrammable computer hardware technology to host machine vision algorithms. Hardware solutions should be specifically designed to support computationally intensive operations and low-latency throughput of large format image data and intermediate floating-point full-frame products. The engineering challenge of such a hardware solution is further compounded for space-based sensor and seeker applications due to the need for computer hardware that is radiation hardened and capable of operating under low SWaP restrictions. Successful proposers will address both the computational and environmental challenges of the envisioned computer hardware solution. 

PHASE I: Demonstrate proof of concept through design, modeling, and/or initial hardware testing. Demonstrate the scalability of the proposed processor hardware technology in order to keep pace with modern large-format imaging sensors, emerging algorithm processing and memory requirements. 

PHASE II: Refine the hardware design and build an initial demonstration hardware prototype for benchtop testing against government furnished sample imagery and processing algorithms. Assess the performance of the prototype hardware in processing the government furnished information (GFI) and provide figures of merit to allow the government to quantify the performance of the developed processing hardware. Support testing of the processing hardware at a government sponsored facility for the purposes of validating the radiation hardened capability of the prototype hardware. 

PHASE III: Integrate the hardware with GFI machine vision algorithms and sensor technology into a government sponsored ground test facility or designated test platform. Provide ground test support, hardware redesigns/upgrades, and integration activities associated with the sensor testbed. 

REFERENCES: 

1: http://www.airforcemag.com/DRArchive/Pages/2017/September%202017/September%2022%202017/STRATCOM-Prepares-for-War-USAF-Looks-to-Give-Airmen-Back-Their-Time-Travis-C-17-Delivers-Aid-to-Mexico.aspx

2:  https://en.wikipedia.org/wiki/Vision_processing_unit

3:  https://docs.house.gov/meetings/AS/AS29/20180417/108171/HHRG-115-AS29-Wstate-GreavesS-20180417.PDF

KEYWORDS: Radiation Hardening, Machine Vision, Space-based Seekers, Computing, Hardware 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop and demonstrate energetic materials for solid rocket motor (SRM) igniters that pass MIL-STD-1751A test criteria to allow MIL-STD-1901A compliance for all electronic in-line initiation. 

DESCRIPTION: The intent of this topic is to explore energetic materials for an ignition system pyrotechnic train that can pass all MIL-STD-1751A test criteria and will allow utilization of an electronic in-line ignition safety device (ISD), thus reducing size, weight, and power (SWaP) and complexity of the ignition system. The ignition system of many solid rocket motors (SRM) contains one or more sensitive pyrotechnic materials, thus requiring an interrupted pyrotechnic train. This typically results in an ISD with physical separation of pyrotechnic elements prior to arming to prevent an unintended ignition. These ISD’s are larger and more complex than desired in-line electronic ISDs. Energetic materials that pass certain test criteria for sensitivity and aging properties must be employed in the pyrotechnic train. The output of the igniter charge (pressurization and thermal input into closed volume) should be equal to or greater than 30 grams of M36 double-based propellant; threshold of equal mass (30 grams) with objective mass of 20 grams; and reaction time equal to or less than that of M36. Use of common initiators such as an exploding foil indicator (EFI) is acceptable but must also pass aforementioned test criteria.  

PHASE I: Develop a proof of concept solution; identify candidate energetics and conduct analyses for predicted performance and sensitivity. Results will be documented for Phase II. 

PHASE II: Expand on Phase I results by conducting test described in MIL-STD-1751A to demonstrate energetic compliance. Design, fabricate, and test a prototype ignition system to validate performance estimates from Phase I. 

PHASE III: The developed solution should be demonstrated via rocket motor ignition and hot-fire testing. Conduct engineering and manufacturing development, test, evaluation, qualification. Demonstration would include, but not be limited to, demonstration in a real system or operation in a system level testbed with insertion planning for a transition program. 

REFERENCES: 

1: Military Standard MIL-STD-1751A, Safety and Performance Tests for the Qualification of Explosives (High Explosives, Propellants, and Pyrotechnics), (DOD, 11 December 2001). Retrieved from, http://everyspec.com/MIL-STD/MIL-STD-1700-1799/MIL-STD-1751A_20891/

2:  Military Standard MIL-STD-1901A, Munition Rocket and Missile Motor Ignition System Design, Safety Criteria For, (DOD, 6 June 2002.) Retrieved from http:>//everyspec.com/MIL-STD/MIL-STD-1800-1999/MIL-STD-1901A_7401/

KEYWORDS: MIL-STD-1901A, MIL-STD-1751A, Propellant, Pyrotechnics, SRM Igniter, Igniter, Ignition Safety Device, ISD, Rocket Motor 

TECHNOLOGY AREA(S): Air Platform, Materials, Space Platforms, Weapons 

OBJECTIVE: Develop an advanced manufacturing technology for constructing integrated thermal protection systems/thermal management systems for use in missiles operating in hypersonic flight conditions. 

DESCRIPTION: This topic seeks an innovative additive manufacturing technology capable of producing thermal protection/thermal management systems for hypersonic flight vehicles which could incorporate dissimilar materials and complex internal shapes such as tubes and channels. Flight vehicles operating at hypersonic speeds experience very high temperatures and very high aerodynamic drag. Temperatures can range from 3,000 degrees F to over 5,000 degrees F on the vehicle’s nose. The leading edges of wings and control surfaces experience 2,000 degrees F to 3,000 degrees F temperatures. Heat transfer from the high temperature exterior surfaces translates into high temperatures on the interior of the flight vehicle which affects the characteristics and performance of structural materials and internal systems. Additionally, the drag forces on vehicles in hypersonic flight can be thousands of pounds. These interrelated challenges must be addressed with a combination of vehicle design, high-performance materials, and innovative manufacturing technologies. 

PHASE I: Develop initial design concept; conduct analytical and experimental efforts to demonstrate a proof-of-principle. Select, design, and develop candidate materials and associated fabrication processes and model or produce/demonstrate “prototype materials” to ensure proof of the basic design concept and functionality. Produce test coupons of the materials and conduct sample scale testing for relevant material properties in ground-based hypersonic aerothermal environment. Perform a manufacturability analysis showing that the materials can be produced in reasonable quantities and at reasonable cost and yields, based on quantifiable benefits, by employing techniques suitable for scaling up. 

PHASE II: Based on the results and findings of Phase I, update/develop and optimize hypersonic Thermal Protection System (TPS) materials selection and processes and conduct detailed testing in a representative hypersonic environment. Demonstrate scalable manufacturing technology during production of the materials. Validate process repeatability and demonstrate the ability of the TPS materials to withstand the simulated aerothermodynamics heating/loading in hypersonic flight environments and to ensure reliability and structural integrity of the proposed materials. 

PHASE III: Expand on Phase II results by optimizing TPS material designs as necessary for integration into a hypersonic defense system/advanced target vehicle. Develop and execute a plan to manufacture the TPS materials developed in Phase II, and assist the transitioning this technology to the appropriate missile defense prime contractor(s) for the engineering integration and testing. Demonstrate performance of candidate materials in relevant hypersonic-type testing of component materials in association with government hypersonic flight test opportunities. Demonstration would include, but not be limited to, demonstration in a missile system or operation in a system level test-bed with insertion/transition planning for a hypersonic missile defense interceptor/target vehicle. 

REFERENCES: 

1: Kehayas N., "Aerodynamically oriented thermal protection system of hypersonic vehicles," United States Provisional Patent Application Appl. No: 62146254, Filed: April 11, 2015

2:  Glass, D.E., et al., "Materials Development for Hypersonic Flight Vehicles," NASA Langley Res https://ntrs.nasa.gov/search.jsp?R=20070004792earch Center, Hampton, VA 23693, Jan 01, 2006, AIAA Paper 2006-8122, https://ntrs.nasa.gov/search.jsp?R=20070004792

3:  Chen, P.C., "Aerothermodynamic Optimization of Hypersonic Vehicle TPS Design by a POD/RSM-Based Approach," 44th AIAA Aerospace Sciences Meeting and Exhibit, 9 - 12 January 2006, Reno, Nevada, AIAA 2006-777

4:  Basu, B., "Ultra high temperature ceramics for hypersonic space vehicles: opportunities and challenges," in "Ultra-High Temperature Ceramics: Materials for Extreme Environment Applications IV", Jon Binner, The University of Birmingham, Edgbaston, United Kingdom, Bill Lee, Imperial College, London, United Kingdom Eds, ECI Symposium Series, (2017), http://dc.engconfintl.org/uhtc_iv/62

5:  Kasen, S.D., "Thermal Management at Hypersonic Leading Edges," A dissertation presented to the faculty of the School of Engineering and Applied Science, University of Virginia in partial fulfillment of the requirements for the degree in Doctor of Philosophy, May 2013

KEYWORDS: Heat Shielding, Hypersonic Aerospace Vehicle, Thermal Protection System, TPS, TPS Design In High Temperature, TPS And Hot Structures, TPS For Hypersonic Aerospace Vehicles, Hypersonic Aerothermodynamics Environment 

TECHNOLOGY AREA(S): Air Platform, Info Systems, Space Platforms, Weapons 

OBJECTIVE: Develop an innovative solution for communicating through the plasma sheath generated around an air vehicle at high Mach number. 

DESCRIPTION: This topic seeks an innovative solution for mitigating/minimizing the effects of the plasma sheath on communications to and from a flight vehicle in hypersonic flight. A flight vehicle traveling through the atmosphere at high Mach number produces a plasma sheath with a high attenuation factor—often leading to full blackout—for standard radio frequencies used in telemetry and other communications. Several approaches that have been considered for mitigation, with varying degrees of success, to include aerodynamic shaping, magnetic window, liquid quenchant injection and solid quenchant mitigation. 

PHASE I: Develop a proof of concept for transmitting and receiving communications signals in the selected frequency bands. Demonstrate through modeling that the proposed technology solution is the most effective and efficient, and most cost-effective for the government to implement. 

PHASE II: Conduct a laboratory demonstration of the proposed communication technology by transmitting and receiving radio frequency signals in the selected frequency bands through a plasma representative of realistic conditions encountered in atmospheric flight at high Mach number. 

PHASE III: Integrate the proposed system into a critical missile system application and generalize the application for broader use across government programs and commercial applications. Demonstrate applicability in one or more element systems, subsystems, or components. The demand for reliable, continuous communications, through a plasma sheath has a wide market appeal for commercial space launch vehicles, defense weaponry, and commercial and defense aircraft. 

REFERENCES: 

1: Catherine Meyers, 16 June 2015, "Communicating With Hypersonic Vehicles in Flight", Journal of Applied Physics, AIP Publishing LLC, 1305 Walt Whitman Road, Suite 300, Melville, NY 11747, https://publishing.aip.org/publications/latest-content/communicating-with-hypersonic-vehicles-in-flight/

2:  E.D. Gilman, J.E. Foster, I.M. Blankson, Feb 2010, "Review of Leading Approaches for Mitigating Hypersonic Vehicle Communications Blackout and a Method of Ceramic Particulate Injection Via Cathode Spot Arcs for Blackout Mitigation NASA/TM-2010-216220", NASA Glenn Research Center, NASA Scientific and Technical Information Program, https://ntrs.nasa.gov/search.jsp

KEYWORDS: Communication Blackout, Radio Signal Blackout, Plasma, Hypersonic Sheath, Reentry Vehicles, Blackout Mitigation 

TECHNOLOGY AREA(S): Air Platform, Info Systems, Sensors, Electronics, Space Platforms, Weapons 

OBJECTIVE: Develop an embedded, high-resolution sensor network for a flight vehicle exterior surface to provide real-time data input to a high-speed vehicle flight control system. 

DESCRIPTION: This topic seeks to develop an innovative high-resolution sensor network to provide real-time data to a vehicle flight control system. Flight vehicles operating at hypersonic speeds experience very high temperatures and aerodynamic forces. These temperature gradients and forces vary in magnitude and direction across the surfaces of the vehicle as it operates over the course of its flight time and profile. The performance of a flight control system would be greatly enhanced by the availability of real-time on-board sensor data. The proposed system must provide data on the surface recession, temperature, pressure, mechanical loads, velocity, etc. based on a network of sensors incorporated into the outer structure of a vehicle. A primary objective of this effort should be the determination of the optimal type, placement and distribution of sensors in the network such that data is available to the flight control system as it is needed. The system must be lightweight, easy to embed/manufacture, capable of withstanding high-temperature (5,000 degrees F), high dynamic pressure, and high mechanical loads. Measurements are to be captured in real-time for input to the flight control system. 

PHASE I: Develop a concept for surface sensor network to include identification of sensor types, number, placement, connectivity, data handling & processing, and interface with a flight control system. Determine processes/procedures for manufacturing/inserting/emplacing sensors into or within the exterior surface of a flight system. Demonstrate through modeling that the proposed technology solution can provide real-time data to the flight control system. 

PHASE II: Develop or obtain representative sensors of each type and test each under conditions representative of flight at high Mach number. Develop a prototype of the surface sensor network integrated into a flight vehicle exterior surface segment and demonstrate the feasibility of the proposed solution in meeting objectives under conditions experienced during flight at high Mach number. Optimize design/components to achieve size, weight, power, cost and durability needs for airborne/space applications. Phase II should conclude with a final design of the innovative solution. 

PHASE III: Integrate the proposed system into a critical missile system application and generalize the application for broader use across government programs and commercial applications. 

REFERENCES: 

1: Michelle Cometa, 6 Feb 2017, "Smart Skins Sensors Are Ready for Takeoff", Rochester Institute of Technology University News, https://www.rit.edu/news/story.php?id=59466

2:  David Szondy, 25 Aug 2014, "BAE Systems Developing "Smart Skin" for Aircraft", New Atlas, https://newatlas.com/bae-smartskin/33458/

3:  Robert R. J. Maier, Institute of Photonics and Quantum Sciences, Heriot-Watt University, Edinburgh, U.K. , 12 Nov 2012, "Embedded Fiber Optic Sensors Within Additive Layer Manufactured Components", IEEE Sensors Journal ( Volume: 13 , Issue: 3 , March 2013 )

KEYWORDS: Embedded Sensor Network, Embedded Sensors Additive Manufacturing, Embedded Thermocouples, Embedded Pressure Sensors, Smart Skins Sensors, Smart Skin Technology, Hypersonic, Instrumentation, Piezoelectric 

TECHNOLOGY AREA(S): Air Platform, Materials, Electronics, Battlespace, Weapons 

OBJECTIVE: Develop lightweight fins to enhance the maneuverability of a high-speed interceptor. 

DESCRIPTION: This topic seeks a design for lightweight, deployable, fins to enhance the maneuverability of interceptors operating within the atmosphere at high Mach number flight speeds. Such interceptors must be capable of precise, agile aerodynamic maneuvering. One method to achieve this requirement is through the advancement of aerodynamic fin design and actuation. The proposed design should include a compact control actuation system that interprets vehicle guidance commands for accurate positioning and control with an extremely fast response time. The proposed design should demonstrate precision maneuverability for a representative axisymmetric missile body in the high hypersonic velocity regime [. The design should be as light as possible while still allowing maximum control effectiveness over the required velocity range; the fin will be exposed to significant aerodynamic and thermal loads during high dynamic pressure operations. The design may also incorporate a fin deployment mechanism, as control surfaces often need to be folded or retracted in some manner in order to facilitate integration within the launch platform, such as a canister. Cost should also be considered since the application will be in expendable vehicles. 

PHASE I: Develop a proof-of-principle concept. Through modeling and analysis, demonstrate the concept can operate with precision maneuverability in the atmosphere in the high hypersonic velocity regime. Provide expected aerodynamic and thermal load performance analysis and cost estimates. 

PHASE II: Develop a prototype meeting government-provided specifications that can be integrated into a missile-sized vehicle and show maneuverability over in the high hypersonic velocity regime. Verify prototype performance via high-fidelity, numerical modeling. 

PHASE III: Mature the prototype via component testing to a system-level test (ground and/or flight tests). 

REFERENCES: 

1: National Research Council of the National Academies, "Making Sense of Ballistic Missile Defense: An Assessment of Concepts and Systems for U.S. Boost-Phase Missile Defense in Comparison to Other Alternatives," 2012.

2:  Victor Giurgiutiu and Radu Pomirleanu, "Smart Material Actuated Missile Flight Control Surfaces Feasibility Study," U.S. Army Research Office, November 2000, (https://apps.dtic.mil/dtic/tr/fulltext/u2/1038103.pdf).

3:  Rank Fresconi, Ben Gruenwald, Tansel Yucelen, and Jubaraj Sahu, "Adaptive Missile Flight Control for Complex Aerodynamic Phenomena," U.S. Army Research Laboratory, August 2017, (https://apps.dtic.mil/dtic/tr/fulltext/u2/a384331.pdf).

KEYWORDS: Aerodynamic Control Surface, Thermal Load, Supersonic Missiles, Missile Steering, Compact Actuation System, Weapons Steering, Divert Control 

TECHNOLOGY AREA(S): Air Platform, Materials, Sensors, Electronics, Battlespace, Space Platforms, Weapons 

OBJECTIVE: Develop a LADAR capability to fit in a small, ruggedized footprint. 

DESCRIPTION: This topic seeks to develop or adapt LADAR capability to fit in a small, ruggedized footprint. Many commercially available LADAR systems can exceed 50 kg and require in excess of 500 watts of power. Conversely, smaller LADAR products with lower weight and power footprints can have challenges with data fidelity and survivability. The desired innovation is the marriage of relevant commercial systems with the ability to survive and perform in stressing environments. Ultimately, it is desirable to develop a capability based on a mature system that is both miniaturized and rugged. The underlying components should be sourced from US companies. The primary function of this LADAR capability will be precision range finding, with a target range should be between 100 and 200 km. The final product should be an adaptable architecture that can be used to enhance other sensor modes. The goal is a package that does not exceed a volume of 0.011 cubic meters and a weight of 5 kg. The main considerations of increased ruggedness should be enhanced survivability through elevated shock and vibration conditions. 

PHASE I: Conduct commercial and technical research and/or experimentation aimed towards reducing size, weight and power while maintaining survivability. The product of this research should be a serviceable plan of action to obtain commercial LADAR product/enabling technologies and arrange them in such a way as to meet mission requirements, resulting in a proof-of-concept design. 

PHASE II: Obtain needed components and fabricate/assemble prototype(s). Develop and implement a testing regimen to further refine the concept and provide evidence that the prototype(s) meet mission requirements. 

PHASE III: Conduct shock and vibration testing to demonstrate survivability. Develop and implement production of finalized/optimized design and place in full scale test. Transition product to government and commercial customers. 

REFERENCES: 

1: http://www.dtic.mil/dtic/tr/fulltext/u2/a488211.pdf

2:  DeFlumere, Michael E., Fong, Michael W., Stewart, Hamilton M. "Dual Mode (MWIR and LADAR) Seeker for Missile Defense" BAE Systems, 29 July 2002

3:  https://apps.dtic.mil/dtic/tr/fulltext/u2/a316077.pdf

4:  https://www.teledyneoptech.com/en/products/airborne-survey/titan/

KEYWORDS: LADAR, LIDAR, Miniaturization, Range-finding, Laser, Sensor, Rugged, COTS 

TECHNOLOGY AREA(S): Air Platform, Info Systems, Ground Sea, Materialssensors, Electronics, Space Platforms, Weapons 

OBJECTIVE: Develop a missile aft antenna that accommodates a centered bulkhead through hole. 

DESCRIPTION: This topic seeks potential physical rearrangement of missile propulsion systems and mechanical structures aboard missiles to ultimately expand the targeted battlespace to satisfy missile defense goals. Conventional centered bulkhead placement of a missile aft antenna (MAA) requires improvement for various applications in order to achieve enhanced maneuverability requirements. The approach is to establish a MAA design/arrangement that accommodates a centered bulkhead through hole, such as conformal antenna placement within a heat shield. The design/arrangement needs to maintain optimal system performance for radio frequency (RF) data transfer through substantial launch, separation, and maneuvering events that have heat and dynamic loads on the vehicle. The design/arrangement will survive exposure to a spectrum of environments consistent with different atmospheric conditions during flight. The new antenna design/arrangement should avoid disrupting the functionality of any other vehicle hardware during flight. The MAA should be operational with multiple bands such as X- and S-Bands to provide aspect angle coverage, radiate and receive radar messages. The MAA would be incorporated as part of a larger missile tactical communication network, including other antennas and a communication transponder capable of receiving uplink and transmitting downlink messages. A new aft antenna would be subjected to strict requirements for frequency and bandwidth in addition to operational survivability conditions.  

PHASE I: Develop a proof concept for a multi-frequency (X- and S-bands) MAA capable of receiving uplink and transmitting downlink messages allowing for a centered aft bulkhead through hole. Verify expected performance through modeling and analysis. 

PHASE II: Develop a prototype that meets government provided specifications and that can be integrated into a missile vehicle and show uplink and downlink performance through dense rocket exhaust plumes. Verify prototype performance through, but not limited to, high-fidelity modeling and Radio Frequency (RF) chamber testing. Deliverable should be a feasible design and corresponding prototype. 

PHASE III: Mature the prototype via component testing to a system-level test (ground and/or flight tests). 

REFERENCES: 

1: http://www.dtic.mil/docs/citations/ADA015630

2:  http://www.dtic.mil/docs/citations/ADA481623

3:  https://ieeexplore.ieee.org/document/1141655/citations#citations

KEYWORDS: Antenna, RF, Radio Frequency, Antenna, Conformal, Multi-band, X-band, S-band, Missile, Multi-frequency 

TECHNOLOGY AREA(S): Weapons 

OBJECTIVE: Develop innovative physics-based modeling methods for predicting high power fiber laser performance given refractive index and doping profile geometries of “as drawn” optical fibers. 

DESCRIPTION: This topic seeks mathematical and physics-based modeling and simulation source codes that import actual fiber refractive index and doping profile geometries to predict fiber performance and to estimate high power performance limitations. The need to model and verify, “as drawn,” fiber parameters to an intended design is critical to extending the laser reliability and power scaling designs beyond current state of the art. This modeling capability is critical to developing next generation high power fiber laser weapon systems as it will extend their efficiency, reliability, and multi-kW power scaling capabilities. Narrow-linewidth all-fiber laser sources are highly desired for directed energy applications, as they can be either spectrally or coherently beam combined for further power scaling to power levels. Develop and demonstrate concepts and hardware which enable high-brightness, high-power scaling of Ytterbium and Thulium fiber lasers/amplifiers to mature components and subsystems for robust system architectures. Fiber refractive index and rare earth doping profiles impact the ability of the fiber optic wave guide to maintain diffraction limited beam quality and produce good beam quality output at high power. Commercial measurement apparatus are available to provide refractive index and doping profile input parameters. Measurement of refractive index and tolerance of refractive index for typical large mode area rare earth doped fused silica fibers can be commercially manufactured with tolerances of 1x10-4, plus or minus 5x10-5. Therefore, refractive index differences between cores and cladding materials are critical parameters when propagating or combining multiple fiber lasers concurrently and is critical to the implementation of advanced beam control architectures. Similarly, non-destructive commercially available approaches can measure distribution and concentration of dopant materials in an optical fiber with measurement by % weight of rare earth dopants in an active fused silica cores to an accuracy of +/- 0.1 percent. 

PHASE I: Develop and mature innovative physics-based modeling and simulation software methods that import as measured refractive index and doping profile geometries of fibers designed and fabricated for high power fiber lasers/amplifiers. Modeling and simulations should incorporate physical configuration geometries and operational performance parameters from actual fiber laser implementations to provide prediction of deleterious effects. 

PHASE II: Expand the physics-based modeling and simulation software methods to include both commercially available and novel optical fibers fabricated for high power fiber lasers. Advanced modeling and simulations should incorporate realistic heating, fiber coiling, and changes to amplifier seeding methods and pumping. Software source codes should demonstrate that physics assumptions incorporate actual measurement parameters including minute changes to refractive index profiles and rare earth doping constituents distributions to verify fiber geometry of single mode, multimode and novel fibers including; conventional large mode area, photonic crystal, and photonic bandgap fibers. 

PHASE III: Commercialize the software and technologies for accurately modeling and predicting deleterious effects in novel fibers designed for high power operation. 

REFERENCES: 

1: Marcuse D. Principles of Optical Fiber Measurement, ch. 4, New York: Academic Press, 1981

2:  Yablon AD and Jasapara J. Hyperspectral optical fiber refractive index measurement spanning 2.5 octaves, SPIE Proceedings, vol. 8601, 86011V, 2013.

3:  Zhao Y, Fleming S, Lyytikainen K, and Poladian L. Nondestructive Measurement for Arbitrary RIP Distribution of Optical Fiber Preforms, Journal of Lightwave Technology, vol. 22, pp 478-486, 2004.

4:  Pace P, Huntington S, Lyytikäinen K, Roberts A, and Love J. Refractive index profiles of Ge-doped optical fibers with nanometer spatial resolution using atomic force microscopy, Optics Express, vol. 12, pp. 1452-1457, 2004.

5:  Dragomir NM, Goh X, and Roberts A. Three-Dimensional Quantitative Phase Imaging: Current and Future Perspectives, SPIE Proceedings, vol. 6861, pp. 686106, 2008.

KEYWORDS: Fiber Laser, Rare Earth Doped Fibers, Optical Fiber Refractive Index, Dopant Modeling 

TECHNOLOGY AREA(S): Sensors, Space Platforms, Weapons 

OBJECTIVE: Develop the enabling technologies required to field an operational exo-atmospheric Neutral Particle Beam (NPB) system. 

DESCRIPTION: This topic seeks lightweight, compact, energy efficient, radiation hardened, components significantly more advanced than technologies demonstrated in the BEAM Experiment Aboard Rocket (BEAR) system flown in 1989 to enable development of NPB system(s) capable of operating in sub-orbital (pop-up) or orbital (space based) mode. A conceptual NPB system would generate, accelerate, focus, and direct a stream of highly energetic electrically-neutral atomic particles, traveling at near the speed of light, unperturbed by the earth’s magnetic field, at exo-atmospheric targets. Particle interactions with target matter can cause damage and generate measurable emissions allowing target characterization. Desired NPB enabling technologies include: • Lightweight, compact, and energy efficient particle accelerators • Compact power sources • Particle neutralizers that exhibit minimal scatter, have extended operational life, and have minimal impact on operating environment • Anion sources, extractors, and injectors • Beam transport, collimator, focusing, steering, sensing, and tracking components • Sensors capable of detecting emissions from targeted objects Proposed efforts may seek to develop any of the above components within the context of a proposed system concept, with emphasis on achieving low size, weight, and power. 

PHASE I: Develop preliminary design for the component(s). Perform Modeling, Simulation and Analysis (MS&A) and/or limited bench level testing to demonstrate the concept and an understanding of the technology. The proof of concept demonstration may be subscale and used in conjunction with MS&A results to verify scaling laws and feasibility. 

PHASE II: Complete a critical design and demonstrate the use of the technology in two or more prototype efforts. Evaluate the effectiveness of the technology or technique. Perform MS&A and characterization testing within the financial and schedule constraints of the program to show the level of performance achieved. 

PHASE III: Demonstrate the product’s performance improvement as compared to the state of the art. Perform analysis to evaluate the ability of the technology to function within a hypothetical NPB system. 

REFERENCES: 

1: O'Shea PG, Butler TA, Lynch MT, McKenna KF, Pongratz MB, and Zaugg TJ. A Linear Accelerator in Space - The BEAM Experiment Aboard Rocket, Proc. of the Linear Accelerator Conf., Albuquerque NM, 1990.

2:  Vretenar M. The Radio Frequency Quadrupole, Contribution to CAS - CERN Accelerator School: Course on High Power Hadron Machines, Bilbao Spain, May 24 - June 2, 2011. http://cds.cern.ch/record/1536736

3:  Humphries, S. Charged Particle Beams (Dover Books on Physics), Reprint edition, April 17, 2013.

4:  Humphries, S. Principles of Charged Particle Acceleration (Dover Books on Physics), Dover Publications, November 21, 2012.

5:  Bloembergen N, et.al. Report to The American Physical Society of the study group on science and technology of directed energy weapons, Rev. Mod. Phys., vol. 59, pp. S1-S201, July 1, 1987.

KEYWORDS: Neutral Particle Beam, Particle Neutralizer, Compact Accelerator, RFQ Accelerator, Particle Beam Control, Gamma Ray Detector, X-ray Detector, Charge Stripper 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a lightweight micro cooling system that integrates with the latest generation of liquid cooling and dehumidification vest garments and is resilient enough to withstand heavy abrasive use under the EOD Bomb Suit (9) while providing unrestrictive movement during EOD operations. 

DESCRIPTION: The EOD Bomb Suit (9) provides the EOD technician protection from fragmentation, blast pressure, heat and light flash, and flame generated by Unexploded Ordnance (UXO) and Electrically Initiated Devices (EID) when conducting Render Safe Procedures (RSP) or disruption procedures on ordnance and/or devices that cannot be attacked remotely [Ref 2]. The bomb suit provides a wide field of vision, flexibility, and mobility and can weigh in excess of 125 lbs. A Self-Contained Breathing Apparatus (SCBA), which provides breathable air regardless of the ambient atmosphere, and an EOD helmet are also worn which add an additional 60 lbs. The time EOD personnel have for conducting disarming procedures can be limited simply by the total weight of their Personnel Protective Equipment (PPE) and lack of adequate cooling. Failure to complete a mission can be catastrophic. Current cooling techniques involve packing ice into a web-like vest and using gravity to allow melted water to go down the upper torso. This SBIR topic seeks innovative approaches for a lightweight micro cooling system that integrates with the latest generation of liquid cooling and dehumidification vest garments [Ref 3]. The cooling system shall weigh no more than 10 lbs. (5 lbs. objective) and be self-powered up to 6 hrs. An ability to attach to auxiliary/supplemental power is also desired. The cooling system shall be able to limit EOD personnel exposure conditions within the bomb suit to 80°F, 50% relative humidity and not drop below 65°F, 10% relative humidity during the 6-hour self-powered timeframe. At a minimum, cooling shall be focused on the torso and core cooling. Target design goals for the system shall be to operate in all climates and environments that may be encountered by Marines such as arctic, desert, jungle, and coastal, and shall not operationally degrade when ambient temperatures are between 125°F and -25°F. The system shall also fully operate in all humidity levels up to 100 percent and must be resistant to the effects of salt/water spray and extreme sand and dust conditions to the extent outlined in MIL-STD-810G [Ref 1]. The cooling system materials shall be structurally resilient to withstand heavy abrasive use under the EOD Bomb Suit (9) [Refs 2, 3]. 

PHASE I: Develop concepts for an EOD Bomb Suit micro cooling system that meets the requirements highlighted in the Description above. Demonstrate the feasibility of the concepts in meeting Marine Corps needs and establish that the concepts can be developed into a useful product for the Marine Corps. Establish feasibility by material testing and analytical modeling, as appropriate. Provide a Phase II development plan with performance goals, key technical milestones, and a technical risk reduction strategy. 

PHASE II: Develop a scaled prototype evaluation to determine its capability in meeting the performance goals defined in the Phase II development plan and the Marine Corps requirements for the EOD Bomb Suit micro cooling system [Ref 4]. Demonstrate system performance through prototype evaluation and modeling or analytical methods over the required range of parameters including 150 deployment cycles. Use the evaluation results to refine the prototype into an initial design that will meet Marine Corps requirements. Prepare a Phase III development plan to transition the technology to Marine Corps use. 

PHASE III: Support the Marine Corps in transitioning the technology for Marine Corps use. Develop a plan to determine its effectiveness in an operationally relevant environment. Support the Marine Corps for test and validation to certify and qualify the system for Marine Corps use. The potential for commercial application and dual use is high. Beyond the Marine Corps and DoD applications, there are federal civilian agencies, law enforcement agencies, firefighting agencies, and emergency responders that can use this type of personal cooling system. Recreational and athletic applications are also a possibility. 

REFERENCES: 

1. Mil-Std-810G, Department of Defense Test Method Standard: Environmental Engineering Considerations and Laboratory Tests; http://www.everyspec.com/mil-std/mil-std-0800-0899/mil-std-810g_12306/; 2. EOD 9 Suit & Helmet; https://www.med-eng.com/Products/PersonalProtectiveEquipment/MedEngEODIEDD/EOD9SuitHelmet.aspx; 3. Public Safety Bomb Suit Standard, NIJ Standard-0117.00; https://www.google.com/url?sa=t&rct=j&q=&esrc=s&source=web&cd=13&cad=rja&uact=8&ved=2ahUKEwibjoWO3-PfAhU1CjQIHbFaAhkQFjAMegQIBRAC&url=https%3A%2F%2Fwww.ncjrs.gov%2Fpdffiles1%2Fnij%2F227357.pdf&usg=AOvVaw3e6J9iwd6KNLLRPyVJXuuc; 4. 2010 ANTHROPOMETRIC SURVEY OF U.S. MARINE CORPS PERSONNEL: METHODS AND SUMMARY STATISTICS; https://apps.dtic.mil/docs/citations/ADA581918

KEYWORDS: EOD Bomb Suit; Micro Cooling System; Personal Cooling; Refrigeration; Explosive Ordnance Disposal 

TECHNOLOGY AREA(S): Ground Sea 

OBJECTIVE: Develop lightweight road wheel technologies, for marine and on/off road complex mission profiles, that use innovative materials, design, and manufacturing processes; reduce scheduling, manpower, and time constraints; and achieve increased cost efficiencies to translate into lifecycle cost reductions. 

DESCRIPTION: Currently, the Assault Amphibious Vehicle-Family of Vehicles (AAV-FoV) platforms (AAVP7A1 personnel variant, AAVC7A1 command and control variant, and AAVR7A1 recovery variant) share the same road wheel component as the U.S. Army Bradley Fighting Vehicle (BFV) (#12358464). The road wheels are made of forged steel integrated with rubber that incur a substantial weight penalty of 2,011 pounds (24 wheels) per vehicle. The Marine Corps seeks the development of a new road wheel, made of strong yet lightweight materials with either abrasion resistance coating or innovative lightweight steel wear plate designed to sustain track center guide’s abrasion impact without track derail concern. This lightweight wheel design should be able to reduce fuel consumption and prolong the rubber tire life, while increasing interval time between maintenance operations. This topic seeks to explore innovative and alternative road wheel system designs for military vehicles. Of particular interest are concepts that satisfy the following criteria: • Reduce road wheel weight by >40% (BFV steel road wheel - 83.8 lbs./pc) • Reduce or eliminate galvanized corrosion concern • Decrease lifecycle cost • Increase time interval between maintenance • Improve maintainability efficiency • Decrease fuel consumption • Improve rubber tire life with min. average life of 2000 miles under AAV-FoV configuration The lightweight road wheel systems shall operate in basic water, and on primary and secondary roads, trails, and cross-country conditions. Basic water conditions are of salt and fresh, open ocean, surf zones, lakes, rivers, streams, marshes, swamps, snow, slush, and ice. Primary roads are high quality paved, secondary pavement, and rough pavement surfaces. Secondary Roads are loose surface, loose surface with washboard and potholes, and Belgian block surfaces. Trails are one-lane, unimproved, seldom-maintained, loose surface roads intended for low-density traffic. Typically trails have no defined road width, large obstacles (rubble, boulder, logs, and stumps), cross ditches, washouts, steep slopes, and no bridging/culverts. Cross-country terrain can consist of tank trails with crushed rock or having large exposed obstacles (rocks, boulders, etc.), but there are no roads, routes, well-worn trails, or man-made improvements. This includes but is not limited to flat desert, marshes, vegetated plains, jungle, dense forest, mountains, and urban rubble. The system shall be operable and maintain Full Operational Capability (FOC) under the operational conditions as follows: • Tracked platform with six stations per side * Roadwheel size: OD 24 inches • Road wheel impact load cases: 3.5g [vertical], 2g [vertical] @ rim edge, 3g [lateral], and combined (2.5g [lateral] + 1.5g [vertical]). 1g = 8000 lbf (nominal vertical load) • Road wheel fatigue load cases: 1g @ rim edge with a minimum 1.55M cycles life; Combined (1.2g[vertical]+.25g[lateral]) with a minimum 1.55M cycles life • Lateral slopes of up to 40% capable of sine wave operation • Ascending / descending grades of up to 60% • Trails grades up through 40% • Maintain 64.37 kph (40 mph) forward speed on level Primary Roads • Accelerate in the forward direction from 0 to 20 mph (32.2 kph) in 10.5 seconds or less on a dry, hard, level surface • Stop within 15.24 meters (50 feet) from the forward speed of 32.2 kph (20 mph) on a dry, hard, level surface with a drift not to exceed 0.91 meters (3 feet) in the actual stopping distance • Capable of 360 degrees pivot steering turn within 45 seconds or less • Discrete obstacle negotiation, including vertical step (36”), gap (8’), and trench crossing • Sustain riverine operation • Ascend a 91 cm (36 inch) vertical obstacle in the forward and backward directions without preparation vehicle • Ambient air temperatures from -51º C (-60º F) to +52º C (125.6º F) 

PHASE I: Develop wheel concepts to reduce weight and to improve the service life of road wheel system by exploring the use of alternative materials, design, maintainability, and manufacturing techniques that meet the requirements outlined in the Description. Develop test methodology for operations in marine environments and rubber tire durability that evaluate the expected life of lightweight road wheel systems. Demonstrate the feasibility of the concept in meeting the Marine Corps requirements. Establish the wheel design feasibility by material sample testing and analytical modeling to deliver the promised performance and capability, as appropriate. Provide a Phase II plan that identifies the verification approach of performance goals, key technical milestones, and addresses technical risks. 

PHASE II: Develop prototypes and a process for testing. Evaluate the prototype to determine if the performance goals defined in the Phase II development plan and the requirements have been met. Demonstrate system performance through full-scale field testing to include durability and environmental performance. Use results to refine the design to optimize the performance. Prepare a Phase III plan to transition the technology to the Marine Corps. 

PHASE III: Complete full-scale application, testing, demonstration, implementation, and commercialization. The Marine Corps could buy future lightweight road wheel system through a Phase III contract if the performer has the manufacturing capacity. The Marine Corps could also use the results of this effort to update standards in future competitive contracts that would facilitate a teaming arrangement with a company that could produce the quantities required for future acquisitions and sustainment. The technologies developed under this SBIR effort would have direct application to other Department of Defense applications including other services’ lightweight road wheel systems on Tactical Vehicles, Heavy Equipment, and Industrial Equipment. The technologies developed under this SBIR topic would be of interest to industrial, agricultural, and recreational vehicles. The technologies would also have applications for large bulldozers, excavators, graders, and farming equipment used in mining, construction and farming industries. 

REFERENCES: 

1. AMCP 706-356, AMC Pamphlet: Engineering Design Handbook – Automotive Series – Automotive Suspensions. U.S. Army Materiel Command: April 1967.; 2. Wong, Jo Yung. “Theory of Ground Vehicles, 4th Edition.” New York: A Wiley-Interscience Publication, 2008.

KEYWORDS: Tanks; Rubber Compounds; Cold Spray Coating; Composite Materials; Reinforcement Rings; Wear Plate; Induction Hardening; Stress Releasing; Coatings; Sprays; Armored Personal Carrier APC; Aluminum; Solid Rubber Wheel; Amphibious; Fuel Savings; Combat Vehicle; Heavy Weight; Component Durability; Reduced Life Cycle Cost 

TECHNOLOGY AREA(S): Materials 

OBJECTIVE: Develop a mobile recycling facility capable of cleaning, drying, and processing thermoplastics into pellets and filament for use in material extrusion equipment such as 3-D printers and injection molders in remote and austere environments. All equipment must fit within an intermodal container (conex). 

DESCRIPTION: Logistics are the fundamental consideration in forward deployment, consuming one-third of the Department of Defense’s budget [Ref 1]. The former Commandant of the Marine Corps said that the U.S. supply lines in Afghanistan “represent an operational vulnerability” and “we are getting hit; we are losing Marines.” Although resupply can take in excess of 45 days, and a 600-warfighter forward operating base (FOB) requires 22 convoy trucks per day to supply the base, the majority of supplies are brought in rather than sourced locally [Ref 1]. Even a small reduction in the amount of supplies that need to be shipped in could greatly impact the warfighter’s safety and logistical costs. In addition, a significant amount of waste/scrap materials is generated on a daily basis on military operating bases. Plastics represent nearly 8% of the total waste, averaging approximately 450 lbs/Marine/yr [Ref 2]. These materials are either recycled or burned in open pit fires, inflicting damage to the environment and personnel health. Additive manufacturing (AM) technologies are critical to maintaining operational readiness of the military by reducing the logistical supply chain dependence and allowing point-of-need manufacturing. Recent research has demonstrated the feasibility of turning plastic waste into 3-D printing feedstock in the laboratory [Ref 3]. Developing such methods to process waste into useful AM feedstocks in-field is expected to have a great impact on many parts of the Marine Corps, as well as other units in remote locations in which re-use of materials could present significant cost and energy savings. More automation of the process is critical to reduce the man-hours and training required. Currently there exists no such land-based automated recycling system (ARS) to reclaim waste plastics and failed 3-D prints into pellets and/or filament for AM or injection molding processes. NASA, together with Tethers Unlimited, have created the Refabricator for recycling select plastics in space [Ref 5]. Limitations of this technology include limited plastic types (Ultem and Acrylonitrile Butadiene Styrene (ABS) only) and low output. In addition, the system is not commercially available. A mobile plastic recycling extrusion laboratory does not exist. This topic seeks the development of an Expeditionary Mobile Recycling Facility (MRF-X) that provides the capability of processing thermoplastics into pellets and filament for use in material extrusion equipment such as 3-D printers and injection molders in remote and austere environments. The MRF-X shall have all equipment housed in a standard or expandable 20-foot ISO container, with proper tie-downs and capable of meeting MIL-STD 810F/G necessary for transport by land and sea. The unit shall contain duct work to support a 60,000 BTU Environmental Control Unit (ECU) and meet OSHA standards of temperature range of 68-76 °F and humidity range of 20-60%. In addition, the power is limited to the power available on a forward operating base, approximately 180 KW for a typical 500-warfighter FOB [Ref 1]. The unit shall have plastic sorting, cleaning, drying and shredding capabilities. Automation of all or part of these capabilities is preferred. In addition, the unit shall have an ARS capable of processing a wide range of thermoplastics from consumer-grade packaging such as polyethylene terephthalate (PET), polypropylene, polyethylene, polystyrene as well as from failed 3-D prints made of materials such as ABS, PLA, Ultem, and Polyether ether ketone (PEEK). The ARS shall melt and reconstitute thermoplastics into 1.75 ± 0.1 and/or 2.85 ± 0.1 mm diameter filament spools or pellets at an output rate exceeding 2 kg per hour. Filament shall have sufficient flexibility to enable spooling, and be free of defects such as particulate debris and air/moisture bubbles. The ARS until should be able to melt plastics with melting temperatures up to 400 °C. Mechanical testing (tensile) should be performed to verify that performance of reconstituted plastics is within expected range based on literature values for polymer type. 

PHASE I: Develop concepts for a mobile plastic recycling facility that meets the requirements described above. Demonstrate the feasibility of the concepts in meeting Marine Corps needs and establish that the concepts can be developed into a useful product for the Marine Corps. Establish feasibility by material testing and analytical modeling, as appropriate. Provide a Phase II development plan with performance goals and key technical milestones, and that will address technical risk reduction. 

PHASE II: Develop a scaled prototype evaluation. Evaluate the prototype to determine its capability in meeting the performance goals defined in the Phase II development plan and the Marine Corps requirements for the mobile plastic recycling facility. Demonstrate system performance through prototype evaluation and modeling or analytical methods over the required range of parameters including numerous deployment cycles. Use evaluation results to refine the prototype into an initial design that will meet Marine Corps requirements. Prepare a Phase III development plan to transition the technology to Marine Corps use. 

PHASE III: Support the Marine Corps in transitioning the technology for Marine Corps use. Develop mobile plastic recycling facility for evaluation to determine its effectiveness in an operationally relevant environment. Support the Marine Corps for test and validation to certify and qualify the system for Marine Corps use. Beyond Marine Corps and DoD applications, federal and international humanitarian aid agencies can use this recycling facility to aid in disaster relief, fabricating essential items at the point-of-need. Local communities, particularly in remote or underdeveloped areas, could use this technology to reduce waste and 3-D print parts to improve their livelihoods and quality of life. Schools and academia could also employ the recycling facility to develop an in-house recycling program to make feedstock to support 3-D printing laboratories. 

REFERENCES: 

1. “Strategic Environmental Research and Development Program (SERDP) Sustainable Forward Operating Bases.” Noblis, 5/21/10, pp.9, 16. https://www.serdp-estcp.org/content/download/8524/104509/file/FOB_Report_Public.pdf; 2. Cosper, S.D., Anderson, H.G., Kinnevan, K., and Kim, B.J. “Contingency Base Camp Solid Waste Generation.” ERDC/CERL TR-13-17, (2013). https://apps.dtic.mil/dtic/tr/fulltext/u2/a613823.pdf; 3. Zander, N.E., Gillan, M.G., and Lambeth, R.H. “Recycled polyethylene terephthalate as a new FFF feedstock material.” Additive Manufacturing, Volume 21, May 2018, pp. 174–182. https://www.sciencedirect.com/science/article/pii/S2214860418300046?via%3Dihub; 4. Kreiger, M. A., Mulder, M. L., Glover, A. G., and Pearce, J. M. “Life Cycle Analysis of Distributed Recycling of Post-Consumer High Density Polyethylene for 3-D Printing Filament.” Journal of Cleaner Production, Volume 70, 2014, pp. 90-96. https://digitalcommons.mtu.edu/cgi/viewcontent.cgi?article=1035&context=materials_fp; 5. Tethers Unlimited. “Refabricator: A Recycling and Manufacturing System for the International Space Station.” http://www.tethers.com/Refabricator.html

KEYWORDS: Ex-Fab; Filament; Polymer; Additive Manufacturing; 3-D Printing; Plastic Recycling; Expeditionary; Mobile Laboratory; Pellets; Acrylonitrile Butadiene Styrene; ABS; Ultem 

TECHNOLOGY AREA(S): Sensors, Electronics, Battlespace 

OBJECTIVE: Develop an innovative and operationally suitable solution for Electronic Warfare Systems (EWS) Programs of Record (PORs) data pre-processing at the tactical edge that, enabled by artificial intelligence (AI) and machine learning (ML) algorithms, must be able to process vast amounts of raw data to detect, track and recommend actions on signals of interest in a complex electromagnetic environment. 

DESCRIPTION: Marine Corps Systems Command (MCSC) provides dismounted EWS for geo-locating, direction finding and countering threats on the ground and in the air. Currently these systems collect vast amounts of raw and unfiltered data that describe signals from electromagnetic sources in the form of individual pulse descriptor words (PDW) – potentially billions per minute. The raw data is then transmitted back to the tactical operations center (TOC) where it is downloaded, processed and analyzed to identify objects and track targets of interest. The sheer amount of raw data being transmitted over limited bandwidth and post-processed at the TOC is not conducive to real-time signal of interest tracking and hinders the Marines’ ability to react to potential threats. The advent of advanced AI and ML techniques, such as Long Short-Term Memory (LSTM) networks, and the availability of open-source software tools (e.g., TensorFlow) and off-the-shelf processing capabilities (e.g., NVIDIA) provides opportunity to more efficiently and effectively process electromagnetic signal data by enabling preprocessing and filtering at the antennae sensor. The ability to detect composite tracks in real time at the tactical edge will reduce the amount of data necessarily transmitted and post-processed at the TOC, resulting in more efficient signal analysis and ultimately improved effectiveness of EWS capabilities. MCSC is seeking a preprocessing solution for dismounted EWS systems. The solution will utilize innovative AI/ML algorithms to process large amounts of raw data (i.e., PDW) and recommend high priority tracks of interest indicative of patterns of life. The AI/ML algorithms will support signal classification to identify benign versus adversary signals based on a signals of interest list. In an operational scenario, a dismounted EWS could collect up to billions of PDW per minute, resulting in potentially millions of tracks. Processing the collected PDW from the electromagnetic environment is complicated by radio frequency (RF) reflections, clutter (e.g., foliage, structures, terrain, birds), and the sheer volume of PDW. The envisioned pre-processing capability should be able to process the PDW in such a way that objects, particularly slow moving or intermittent signals, can be automatically filtered from clutter and identified as a high priority for further analysis. Requirements for the preprocessing solution are as follows: Demonstrate a preprocessing capability to: (1) track very slow moving objects (0-40mph); (2) track objects among slow (0-40mph) moving point clutter (e.g., birds and insects); and (3) identify and rejoin intermittent or disjointed tracks in a highly complex electromagnetic environment. Each capability listed above should be demonstrated with a representative test case commensurate with the volume and complexity of data likely encountered in the battlespace. The solution must have sufficient time difference of arrival (TDOA) granularity to be able to draw out multiple tracks at once from billions of data points. The system shall have a Signal of Interest (SOI) false alarm rate no greater than 5% (Threshold) and no greater than 2% (Objective) within any 24-hour period of time. The hardware, software, or combined hardware/software solution must be easily integrated with a dismounted backpack-sized EWS, such as the current MODI II, and be antenna agnostic. A representative standard gain antenna should be used for demonstration purposes. The system shall be no larger than 12” by 6” by 4” (not including an antenna) and weighing no more than 5 lbs. not including the battery (Threshold) and no more than 5 lbs. including the battery (Objective). The preprocessor messaging shall be Joint Interface Control Document (JICD) 4.2 compliant. The solution should utilize commercial off-the-shelf hardware and software to the maximum extent possible. Proposals must describe the envisioned processing solution to include the software, hardware or combined approach. The proposer should also indicate expected size, weight, false alarm rate, classification performance, and memory requirements. Software or firmware shall meet cybersecurity requirements. The Phase I effort will not require access to classified information. If need be, data of the same level of complexity as secured data will be provided to support Phase I work. Work produced in Phase II may become classified. Note: The prospective contractor(s) must be U.S. Owned and Operated with no Foreign Influence as defined by DOD 5220.22-M, National Industrial Security Program Operating Manual, unless acceptable mitigating procedures can and have been implemented and approved by the Defense Security Service (DSS). The selected contractor and/or subcontractor must be able to acquire and maintain a secret level facility and Personnel Security Clearances, in order to perform on advanced phases of this contract as set forth by DSS and the Marine Corps in order to gain access to classified information pertaining to the national defense of the United States and its allies; this will be an inherent requirement. The selected company will be required to safeguard classified material IAW DoD 5220.22-M during the advance phases of this contract. 

PHASE I: Develop concepts for an automatic track generation that can be integrated with dismounted EWS, such as the MODI II [Ref 5], and that meets the requirements described above. Demonstrate the feasibility of the concepts in meeting Marine Corps needs through modeling and simulation. Establish that the concepts can be developed into a useful product for the Marine Corps. Provide a Phase II development plan with performance goals and key technical milestones, and that will address technical risk reduction. This Phase II plan will include specification for a prototype. 

PHASE II: Develop a scaled prototype integrated with a standard gain antenna for evaluating purposes and with data inputs representative of dismounted EWS PDW volume and complexity. Evaluate the prototype to determine its capability in meeting the performance goals defined in the Phase II development plan and the Marine Corps requirements for automatic track generation preprocessing. Demonstrate system performance through prototype evaluation and modeling or analytical methods that demonstrate the preprocessing capability with a test case for each of the three demonstration requirements listed in the Description. Use evaluation results to refine the prototype into an initial design that will meet Marine Corps requirements. Prepare a Phase III development plan to transition the technology to Marine Corps use. It is probable that the work under this effort will be classified under Phase II (see Description section for details). 

PHASE III: Support the Marine Corps in transitioning the technology for Marine Corps use, including testing and validation to certify and qualify the system. Develop a ruggedized automatic track generation pre-processor for integration and evaluation to determine its effectiveness in an operationally relevant environment. AI- and ML-enabled processing has potential use in a variety of commercial applications, including speech and handwriting recognition, communications, stock market predictions, robotics and autonomy. Other Government agencies with the need to identify and track objects or trends in complex environments, such as the Federal Aviation Administration, Federal Communications Commission, Customs and Border Protection, and the Federal Bureau of Investigation, could adapt this technology for insights and efficiencies to their particular missions. 

REFERENCES: 

1. Gers, Felix, Schmidhuber, Jürgen & Cummins, Fred. “Learning to Forget: Continual Prediction with LSTM. Neural computation.” Neural Computation, October 2000, 12(10)2451-71. 10.1162/089976600300; 2. Greff, K., Srivastava, R., Koutnik, J., Steunebrink, B. and Schmidhuber, J. “LSTM: A Search Space Odyssey.” IEEE Transactions on Neural Networks and Learning Systems, 2016. https://arxiv.org/abs/1503.04069; 3. 2018 U.S. Marine Corps Science & Technology Strategic Plan. https://www.onr.navy.mil/-/media/Files/About-ONR/2018-USMC-S-and-T-Strategic-Plan.ashx?la=en&hash=73B2574A13A8EC6AAE60CF4670E05C6F97309B8F; 4. Electronic Warfare. Marine Corps Reference Publication 3-32D.1, United States Marine Corps Publication Control Number144 000246 00. 02 May 2016. https://bookpdf.services/downloads/marine_corps_reference_publication_mcrp_3_32d_1_formerly_mcwp_3_40_5_electronic_warfare_2_may_2016.pdf; 5. “Counter Radio-Controlled Improvised Explosive Device (RCIED) Electronic Warfare (CREW).” United States Marine Corps, 12 July 2018. The Official Website of the United States Marine Corps. http://www.candp.marines.mil/Programs/Focus-Area-4-Modernization-Technology/Part-7-Force-Protection/CREW/

KEYWORDS: Electronic Warfare; Electromagnetic Spectrum; Signal Processing; Machine Learning; Artificial Intelligence; Neural Network; Recurrent Neural Network; Long Short-term Memory; Composite Tracker; Pulse Descriptor Word; NVIDIA; TensorFlow 

TECHNOLOGY AREA(S): Ground Sea 

OBJECTIVE: Develop a family of foreign object damage (FOD) mitigation equipment (F2ME) that increases the ability of aircraft to operate in austere environments, reduce engine repair cost, and enhance aircraft sortie rates through FOD prevention. 

DESCRIPTION: The Marine Corps requires a debris mitigation system capable of removing or relocating foreign objects from aircraft operating surfaces at main air bases, air facilities, and Forward Arming and Re-fueling Sites (FARPs) at CONUS and OCONUS locations. The current Marine Corps FOD mitigation capability is not configured properly with adequate equipment to provide the necessary support for all Marine Corps and Joint aircraft platforms in support of the Marine Corps Operating Concept (MOC). Recent analysis outlines growing cost and decreased flight hours/operations due to FOD incidents. The amount of debris and required timelines for removal is disproportionate to our current FOD mitigation equipment capabilities in support of operational concepts and at our expeditionary aircraft training sites, thus reducing the air combat element support forward and their ability to train pilots. This effort should capitalize on new techniques and procedures that will provide more durable expedient debris removal in a shorter time; Reference 1 is a study that can be used as a reference to characterize foreign object debris that may be found on a runway. The F2ME capability must take advantage of modern developments in debris removal equipment, must be easily deployable, must be flexible enough to work in all geographic locations and environments, and provides the capability to quickly remove debris from concrete, asphalt, and airfield surfacing materials (AM2). The F2ME supports the deployment, employment, sustainment and redeployment of the Marine Corps aviation assets across the full range of military operations. Reference 1 identifies key attributes of an airport foreign object debris management program, as well as equipment considerations. The F2ME capability must be able to support USMC and Joint aircraft; operate in extreme cold/hot environments; and be easily transportable, modular, lightweight, and efficient. The F2ME capability must be able to clear, at a minimum, 7,500 sq ft of aircraft operational area per minute using towable/driven systems (pre-operational) and 1,500 sq ft per minute using man-portable systems (rapid response between sorties). It is envisioned that a F2ME will encompass equipment that will be consumable (towable mats) along with robust equipment (i.e., vehicles, tow hitches, and blowers). Summary of capabilities: • Capable of removing debris on aircraft operational surfaces in support of USMC aircraft and various joint platforms • Operate in expeditionary environments, per MIL-STD 810F/G • Transportable by strategic and tactical, air, land, and sea assets • Containerized for ease of use, scalability, and employment Desired System attributes: (1) Debris Removal Capability. The F2ME shall contain equipment capable of removing debris from an airfield surface without causing damage, to include surfaces consisting of aluminum matting generation 2 (AM2), at the following rates: - 6,500 square feet per minute (sq ft/min), Threshold (T), 7,500 sq ft/min, Objective (O); - Landing surface with joints, fractures, and/or aircraft tie-down areas at a rate of 3,500 sq ft/min (T), 4,500 sq ft/min (O); - Man-portable configuration on an individual aircraft landing site in a remote location at a rate of 1,500 sq ft/min (T), 2,500 sq ft/min (O); Marines conducting FOD mitigation operations require equipment that can quickly and efficiently remove FOD from landing surfaces of various sizes and locations. (2) Debris Removal Effectiveness. The FOD Mitigation vacuum shall pick up and retain 94% (T=O) by weight of all debris in its path. All vacuum capable F2ME shall be certified to the Environmental Protection Agency air quality standard of Particulate Matter 10 (PM-10) T=O. The FOD Mitigation friction mat shall be capable of collecting 95% (T), 98% (O) of all debris in its path. The FOD Mitigation debris blowers (towed and man-portable) shall each be capable of relocating 95% (T), 98% (O) of all debris in its path. Consult the Federal Specification for Airfield Runway Sweeping reference 32 for a list of the materials utilized to test the effectiveness of debris collecting equipment [Ref 3]. Marines conducting FOD mitigation operations require equipment that can effectively remove FOD from landing surfaces of various types and conditions. (3) Cleanout. The F2ME vacuum and sweeping components shall be designed to facilitate rapid cleanout of debris by an individual person in less than 5 minutes (T), 3 minutes (O). Rapid cleanout of debris will allow a quicker turnaround of FOD mitigation resources. (4) Battery Power. The F2ME shall utilize direct current battery power for all man-portable, expeditionary components equipped with a motor, with a runtime of at least 30 minutes (T) and 45 minutes (O). The quantity of batteries provided with each component shall be sufficient to provide at least 2 hours of continued use (T=O). The F2ME shall require no more than 600 Watts to recharge batteries, via 120VAC/220 VAC 50-60 Hz source, of equipment powered by direct current (T=O). Battery powered equipment emits less of an audible signature than equipment powered by internal combustion engine and reduces the burden of maintaining additional fuel in an expeditionary environment. Expected battery life is 3 years (T) or 5 years (O). (5) Fuel Required. The F2ME components that have internal combustion engines shall utilize the current approved diesel fuel (JP8/F24) (T=O). The F2ME shall have fuel tank ports compatible with Marine Corps and NATO dispensing nozzles; and shall have fuel ports capable of accepting fuel from a 5-gallon can (T = O). Man-portable platforms may use standard military gasoline. The platforms must be capable of operating on standard military fuel and accepting fuel from standard means. (6) Weather. The F2ME shall be capable