Multiband Array Radiators

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8718-07-C-0045
Agency Tracking Number: F061-205-0637
Amount: $736,222.00
Phase: Phase II
Program: SBIR
Awards Year: 2007
Solicitation Year: 2006
Solicitation Topic Code: AF06-205
Solicitation Number: 2006.1
Small Business Information
2790 Indian Ripple Road, Russ Research Center, Dayton, OH, 45440
DUNS: 603299207
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Daniel Reuster, PhD.
 Director of Engineering
 (937) 320-5999
Business Contact
 Jerry Capozzi
Title: President / COO
Phone: (937) 320-5999
Research Institution
A program involving analysis and design, reinforcement materials research and development, composite fabrication, and composite property testing is proposed here to develop improved interlaminar properties of carbon-carbon composites used as the substrates for rocket propulsion components, such as exit cones and nozzle throats. The improved interlaminar properties must be obtained with minimal impact on the in-plane properties of the C-C composites. The most important technical objective that must be achieved to satisfy the primary objective of the proposed program is the successful further development of the concept of the discontinuous carbon fiber reinforcement interleaf material manufactured by Energy Sciences Laboratories, Inc. (ESLI) on San Diego, CA. The focus of the ESLI reinforcement interleaf material development is to achieve high interlaminar properties, low impact on in-plane properties, manufacturing scale-up to reasonable sizes, and cost affordability. A measure of success is the magnitude of interlaminar reinforcement properties improvement for similar impact on in-plane properties relative to competing technology such as stretch-broken fabric and needled fabric preforms. To provide the best assessment of the reinforcement interleaf technique to enhanced interlaminar properties, the proposed Phase II effort will procure stretch-broken and needled fabric reinforcement, along with continuous 2D carbon fabrics. C-C composites will be fabricated using no interlaminar reinforcement, two different types of reinforcement interleaf materials developed and fabricated by ESLI, stretch-broken fabric and needle-punched fabric. Mechanical property measurements, including both in-plane and interlaminar properties, will be performed to enable an assessment of the improved interlaminar properties and the reductions in in-plane properties associated with all of these composites. Finally, C-C exit cone designs will be developed for all of these reinforcement methods and their associated composite properties, to determine an analytical assessment of the minimum weight design achieved by the various reinforcement methods. BENEFIT: Enhanced interlaminar strength C-C composites, provided they are obtained with minimal impact on the C-C in-plane properties, may find immediate application in rocket propulsion components such as nozzles and exit cones. If the high interlaminar strength, high in-plane strength C-C composites can be achieved, remaining hurdles to their implementation will include 1) fabrication scale-up to production sizes and quantities; 2) the economics of this approach relative to the competitive methods for achieving enhanced interlaminar properties; and 3) the resources required for qualification of the reinforcement for the target rocket propulsion components. Challenges to the implementation of the proposed interlaminar reinforcement exist but would not be insurmountable with sufficient technical and cost incentives. Beyond the C-C rocket nozzle applications, there are a host of other C-C composite components that would benefit from the proposed interlaminar reinforcement technology. Thermal protection system (TPS) components, both for the airframe and for the propulsion components, of USAF-envisioned space access and current and future missile vehicles would be other near term applications that would directly benefit from the proposed technology. These TPS components include the leading edges of vehicle wings and missile fins, acreage region TPS panels, and control surfaces such as rudders, flaps, aerolons, and elevators. The proposed technology, if successful in C-C composites, would likely be equally successful if implemented within other carbon fiber reinforced composite materials, both low temperature (i.e., organic matrix) and high temperature (e.g., ceramic matrix composites such as silicon carbide, hafnium carbide, zirconium carbide, etc.). The range of applications associated with continuous reinforcement carbon fiber composites of other matrix forms is significant.

* information listed above is at the time of submission.

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