Scramjet Propulsion Technologies

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics; Advanced Infrastructure & Advanced Manufacturing 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: Advance scramjet propulsion technologies to extend the range of propulsion systems for the missile defense system. DESCRIPTION: MDA is interested in increasing the time, range, and defeat opportunities of future missile systems by replacing the traditional upper stage with scramjet technology. The goals of this topic are to identify the engagement advantage of using scramjets as interceptor upper stages and advance technologies to improve scramjet performance. Scramjet advantages to study include potentially longer loiter system for earlier engagements, more maneuverability through mid-course, and enabling other defeat opportunities. Technologies should improve scramjet performance through increased maneuverability, maximization of operational envelope (including low and high altitudes and low and high velocities), minimization of mass and volume, and maximization of total impulse. Specific technologies to advance include (but are not limited to) 1) Higher endothermic capacity synthetic fuels to enhance scramjet heat exchange capability and reduce coking onset; 2) storage solutions that enable use of hydrogen fuel, 3) More robust, less expensive ignition systems; and 4) Scramjet measurement/diagnostics sensors readily applicable to ground and flight test; 5) Advanced high-temperature, hypersonic-capable materials for use in solid-state fabrication of inlet and fluid dynamics components for scramjet applications; 6) Near/net-shape inlet and fluid dynamic components for scramjet applications; and 7) Cost effective thermal barrier coating processes and/or materials for internal flow paths. All solutions must assume 20 year shelf life with fully loaded interceptor and simplified deployment logistics consistent with military munitions. PHASE I: Phase I-like proposals will not be evaluated and will be rejected as nonresponsive. For this topic, the Government expects the small business would have accomplished the following in a Phase I-like effort via some other means, e.g., independent research and development (IRAD) or other source, a concept for a workable prototype or design to address, at a minimum, the basic capabilities of the stated objective above. Proposal must show, as appropriate, a demonstrated technical feasibility or nascent capability. The documentation provided must substantiate the proposer's development of a preliminary understanding of the technology to be applied in their Phase II proposal in meeting topic objectives. Documentation should comprise all relevant information including, but not limited to, technical reports, test data, prototype designs/models, and performance goals/results. Feasibility = maturity and what have you already done/validated. Proposers interested in participating in Direct to Phase II must include in their responses 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 a proof of concept like Phase I component and/or other validation in a relevant environment, and/or at a much higher TRL level (5 or higher) and describe the potential commercialization applications. The documentation provided must validate that the proposer has completed development of technology in previous work or research completed.) IRAD work, previous Phase I/Phase II work: Documentation should include the most relevant information including, but not limited to: technical reports, test data, prototype designs/models, and/or performance goals/results. Work submitted within the feasibility documentation must have been substantially performed by the proposer and/or the principal investigator (PI). PHASE II: Efforts must include system-level trade studies and intercept engagement analysis utilizing scramjet as an upper stage. Compare performance with a throttling rocket motor upper stage. Intercept engagement studies do not need to include endgame. Discuss assumptions with government representatives. Utilize system level trades to inform technology and component requirements. Develop and demonstrate new technologies to improve scramjet performance. Proposals should identify one or more technologies to advance. Conduct testing of the technology(ies) in relevant environment, and implement changes as necessary. PHASE III DUAL USE APPLICATIONS: Partner with a system integrator to determine relevant design sizes and to demonstrate the technologies developed in phase II in a representative environment. REFERENCES: 1. A. Kumar, Numerical Simulation of Scramjet Inlet Flow Fields, NASA, 1986. 2. P. J. Drummond, M. Bouchez and C. R. McClinton, Overview of NATO Background on Scramjet Technology, Langley Research Center, 2006. KEYWORDS: Propulsion; Hypersonics