OUSD (R&E) MODERNIZATION PRIORITY: General Warfighting Requirements (GWR); Hypersonics; Space TECHNOLOGY AREA(S): Battlespace Environments;Materials / Processes; Weapons 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 the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: Develop a weather-resistant, conductive Thermal Protection System (TPS) material, which can survive hypersonic flight environments and is manufactured by methods/processes with high uniformity/reproducibility. DESCRIPTION: Current generation hypersonic vehicle Thermal Protection System (TPS) materials provide adequate thermal resistance but have limited structural capability in all-weather environments and a low level of manufacturing sophistication. This leads to high levels of variability and introduces program and performance risk. Hypersonic vehicles experience temperatures in excess of 3000 F and encounter elevated levels of shock and vibration. These vehicles must also be able to fly through all types of weather and withstand precipitation at high speeds. Developing and integrating conductive TPS materials capable of withstanding the harsh environments and weather experienced through flight is a priority for enhancing performance in hypersonic vehicles. Proposers should utilize publicly available data on hypersonic flight conditions when identifying material solutions, specific requirements will be provided in the Phase II. Material solutions that could yield agile configurations with tailored conductivity throughout the TPS would provide more versatile hypersonic vehicles. While proposed materials must meet thermal, dielectric, mechanical and conductive specifications, solutions must also maintain uniformity when manufactured in bulk and ensure ease of assembly. Solutions proposed to this SBIR topic should apply some of the advanced aerospace composite materials and manufacturing technology developed over recent years; including but not limited to: fiber reinforcement, fiber orientation, ultra-high temperature ceramics, high-temperature dielectrics, and additive manufacturing to develop reliable, uniform, thermally conductive/high strength materials and near-net shape components in form-factors applicable to Navy hypersonic flight vehicles. Specific form factors and requirements are held at higher distribution levels and shall be provided upon contract award as applicable. 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 Counterintelligence Security Agency (DCSA). The selected contractor must be able to acquire and maintain a secret level facility and Personnel Security Clearances, in order to perform on advanced phases of this project as set forth by DCSA and SSP 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 advanced phases of this contract. PHASE I: Demonstrate a proof of concept for conductivity and structural capability of materials/manufacturing solutions at the desk top/lab scale level. Figures of merit for consideration and to be defined are dielectric properties, physical density, mechanical and compressive strength, and in-plane/through thickness thermal conductivity up to 3000 F. Address manufacturing approaches, uniform producibility concerns, and scale-up potential for production of aerospace grade hardware. The Phase I Option, if exercised, will include the initial design specifications and capabilities description to build a prototype solution in Phase II. PHASE II: Produce prototype hardware to the requirements, materials, form factors and manufacturing approaches defined from Phase I. Further material, thermal and mechanical characterization data shall also be provided in order to assess replacement risk against current incumbent materials. At the end of Phase II, prototype hardware will be provided for government evaluation in a relative hypersonic environment. It is probable that the work under this effort will be classified under Phase II (see Description section for details). PHASE III DUAL USE APPLICATIONS: Support the Navy in transitioning the technology for Navy use. The final product shall be a prototype and design package outlining the material and manufacturing/assembly methods. A suitable material solution and assembly method is required for the future system to ensure reliability and performance throughout flight. This technology can be transitioned to Navy and Air Force hypersonic and ballistic re-entry weapon systems. Solution materials would have applicability in commercial access-to-space environment as well as commercial aerospace, and gas turbine engine applications. REFERENCES: Soboyejo, W. O., Obayemi, J. D., & Annan, E. (2015). Review of High Temperature Ceramics for Aerospace Applications. Advanced Materials Research, 385-407. https://www.researchgate.net/publication/287972274_Review_of_High_Temperature_CeramCer_for_Aerospace_Applications Randy J. Tobe, Ramana V. Grandhi. Hypersonic vehicle thermal protection system model optimization and validation with vibration tests. Aerospace Science and Technology, Volume 28, Issue 1, 2013, Pages 208-213, ISSN 1270-9638. https://www.sciencedirect.com/science/article/pii/S1270963812001824 Glass, David. Ceramic Matrix Composite (CMC) Thermal Protection Systems (TPS) and Hot Structures for Hypersonic Vehicles. 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 14 June 2012. https://doi.org/10.2514/6.2008-2682 Yang, Ya-zheng; Yang, Jia-ling; Fang, Dai-ning. Research progress on thermal protection materials and structures of hypersonic vehicles. Applied Mathematics & Mechanics, Jan2008, Vol. 29 Issue 1, p51-60. 10p. 3 Diagrams. https://link.springer.com/article/10.1007/s10483-008-0107-1?utm_medium=affiliate&utm_source=commission_junction&CJEVENT=b5d1b098839f11ec81eedac00a82b836&utm_campaign=3_nsn6445_deeplink&utm_content=en_textlink&utm_term=PID100357191erLink KEYWORDS: Weather-Resistant Materials; Thermal Protection System; Manufacturability; High Thermal Materials; Thermal Resistance; Reentry Vehicles; Hypersonic Vehicle Heat Loads; Conductive Materials.
