Lightweight High Thrust Propulsion Technology for Interceptors

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Space Technology 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 technologies to maximize performance of lightweight propulsion systems for interceptors. DESCRIPTION: This topic seeks propulsion system technologies for axial systems and/or divert and attitude control systems (DACS). The proposed technologies must be capable of surviving in multiple environments including 20 years ground based deployment or 5 years low earth orbit (LEO) deployment. This topic does not specify propellant or fuel/oxidizer type beyond service life and performance capability considerations. Hydrazine based monopropellants and bi-propellants are the current state of the art highest performance propellants. This topic desires technologies that increase performance of hydrazine-based systems or disruptive new technologies that surpass them. For example, solutions could minimize inert mass or enable use of mixed oxides of nitrogen (MON) compositions with low nitric oxide mass fractions to maximize performance. Disruptive solutions could be new chemistries or propulsion designs that dramatically surpass existing performance. Key performance metrics include propellant mass fraction, specific impulse, high thrust to weight ratio, short ignition delay, long duration duty cycles, low minimum impulse bit, and ability to maintain center of gravity control. 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: 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: Develop and test propulsion technologies for a propulsion system with axial thrust and/or divert and attitude control. Proposals may focus on components or full propulsion system. Proposals focusing on component technologies should demonstrate technology capability early in the period of performance, and enable a path to full system demonstration within 2 years through other efforts if necessary. Demonstration of the system outside of ambient temperatures is not required, but the system must be capable of operating between -20C and 60C. The final propulsion system must have a thrust to weight ratio of at least 8 for the axial thrust and/or 5 for the divert thrust. System designs that minimize the unit cost would be preferred. PHASE III DUAL USE APPLICATIONS: Work with propulsion system manufacturers/designers to implement the propulsion system with propellant formulation and manufacturing of propulsion system into a full-scale testing of a flight-weight system. A successful Phase III would provide the necessary technical data to transition the technology into a missile defense application. REFERENCES: https://ntrs.nasa.gov/citations/19780005279 https://ntrs.nasa.gov/api/citations/19720019028/downloads/19720019028.pdf https://commons.erau.edu/cgi/viewcontent.cgi?article=1101&context=edt KEYWORDS: Propulsion; Space; Propellant; Lightweight; Interceptor; Thrust