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The Award database is continually updated throughout the year. As a result, data for FY24 is not expected to be complete until March, 2025.

Download all SBIR.gov award data either with award abstracts (290MB) or without award abstracts (65MB). A data dictionary and additional information is located on the Data Resource Page. Files are refreshed monthly.

The SBIR.gov award data files now contain the required fields to calculate award timeliness for individual awards or for an agency or branch. Additional information on calculating award timeliness is available on the Data Resource Page.

  1. The Integrated Computational Environment for Airbreathing Hypersonic Flight Vehicle Modeling and Design Evaluation

    SBC: Advanced Engineering Solutions            Topic: T201

    An integrated computational environment for multidisciplinary, physics-based simulation and analyses of airbreathing hypersonic flight vehicles will be developed. These vehicles are among the most promising alternatives for the next generation of Highly Reliable Reusable Launch Systems (HRRLS). The proposed work will enable development of models with varying fidelity, incorporating the coupled dyn ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  2. Passive Wireless SAW Humidity Sensors

    SBC: SENSANNA INC.            Topic: T601

    This proposal describes the preliminary development of passive wireless surface acoustic wave (SAW) based humidity sensors for NASA application to distributed humidity monitoring systems. SAW devices are a platform technology for passive wireless sensing of numerous possible measurands. SAW devices have been demonstrated as passive wireless temperature sensors in NASA contracts NNK04OA28C and NN ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  3. Turbopump Design for Deep Throttling Capability

    SBC: Barber-Nichols, LLC            Topic: T802

    A rocket engine turbopump design using a partial emission pump combined with a zero net positive suction pressure inducer design is proposed to achieve a robust, deep throttling capability in 5k to 15k lbf thrust range rocket engines. A partial emission pump can provide better low-flow/thrust stability at a better efficiency than full emission pumps in this throttle range. A zero net positive suc ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  4. Microwave Detection of Laser Ultrasonic for Non-Destructive Testing

    SBC: BOSSA NOVA TECHNOLOGIES, LLC            Topic: T701

    In this proposal, we describe a program to develop a high-performance, cost-effective and robust microwave receiver prototype for multi-purpose Non-Destructive Evaluation (NDE). Currently, NDE of space transportation vehicles is primarily carried out on the ground, between missions. For future space missions, as duration and frequency increases, more inspection will need to be performed in space ...

    STTR Phase II 2008 National Aeronautics and Space Administration
  5. Development of Novel, Optically-Based Instrumentation for Aircraft System Testing and Control

    SBC: BRIMROSE CORPORATION OF AMERICA            Topic: T202

    We propose to design, build and evaluate a prototype of a compact, robust, optically-based sensor for making temperature and multi-species concentration measurements in propulsion system ground and flight test environments. This system will utilize a widely tunable near infrared light source to make absorption measurements of combustion reactant and products in the combustion zone (with accuracy f ...

    STTR Phase II 2008 National Aeronautics and Space Administration
  6. An On-Chip Nano-Plasmonics Based Urine Protein Assay Cartridge

    SBC: CFD RESEARCH CORPORATION            Topic: T302

    Long-term exposure to microgravity and radiation during space exploration can pose a critical threat to the health of a flight crew. Real-time monitoring of urine protein levels is an effective way to follow the onset and progress of many diseases and guide the prompt selection of proper therapy. The success of such diagnostic tasks, which is strongly desired for flight missions, critically depend ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  7. Fuel/Oxidizer Injector Modeling in Sub- and Super-Critical Regimes for Deep Throttling Cryogenic Engines

    SBC: CFD RESEARCH CORPORATION            Topic: T802

    Accurate CFD modeling of fuel/oxidizer injection and combustion is needed to design and analyze liquid rocket engines. Currently, however, there is no mature modeling capability for liquid fuel/oxidizer injectors in LOCI-Chem, used by NASA and its contractors to analyze rocket engines. In this STTR, an innovative, high fidelity injection module will be developed that features the Level Set (LS) i ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  8. Numerical Simulation of Rocket Exhaust Interaction with Lunar Soil

    SBC: CFD RESEARCH CORPORATION            Topic: T602

    Rocket plume impingement can cause significant damage and contaminate co-landing spacecraft and surrounding habitat structures during lunar landing operations. CFDRC and the University of Florida will develop an innovative simulation system for predicting surface erosion and debris transport caused by lunar surface rocket plume impingement. This simulation system combines 1) a unified continuum-ra ...

    STTR Phase II 2008 National Aeronautics and Space Administration
  9. A Reusable, Oxidizer-Cooled, Hybrid Aerospike Rocket Motor for Flight Test

    SBC: ROLLING HILLS RESEARCH CORP            Topic: T202

    The proposed innovation is to use the refrigerant capabilities of nitrous oxide (N2O) to provide the cooling required for reusable operation of an aerospike nozzle in conjunction with an N2O-HTPB† hybrid rocket motor. The phase change cooling as liquid N2O is flashed into a vapor is crucial to limiting to acceptable levels the erosion of both the nozzle throat and spike, thereby enabling reusabl ...

    STTR Phase I 2008 National Aeronautics and Space Administration
  10. Low Erosion Ceramic Composite Liners for Improved Performance of Ablative Rocket Thrust Chambers

    SBC: Hyper-Therm High-Temperature Composites            Topic: T801

    Advanced liquid rocket propulsion systems must achieve longer burn times without performance degradation to allow the lowest cost per kilogram access to space. Ablative thrust chambers have an extensive heritage and are the low cost approach to fabricating rocket thrust chambers. However, composite ablative chambers suffer from erosion that typically limits performance of the engine in terms of bu ...

    STTR Phase I 2008 National Aeronautics and Space Administration
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