MDA27BZ02-DV006 — Performance Enhancement of Solid Rocket Motors Applied to Existing Systems

Develop and demonstrate enhanced capability/performance of a Solid Rocket Motor (SRM) on an existing missile system without changing system form factor.

The Missile Defense Agency designs, develops, and delivers advanced missile defense capabilities to protect the United States, its allies, and deployed forces from missile attacks in all phases of flight. Traditional SRM propellant formulations and motor designs are mostly optimized, creating some limitations in regards to capability when form factor is constrained [1]. Methods to enhance and optimize the performance of SRM technology at reasonable cost have been researched for decades, incorporating a variety of potential solution paths such as burn-rate enhancement, particle size modifications, propellant composition optimization, and more [2]. Performance enhancements of SRMs in existing missile systems are desired to provide increased capability to both defensive systems and target systems used to validate defensive capabilities.

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 Technology Readiness Level (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).

Under this Direct to Phase II effort, successful proposals should develop and demonstrate enhanced capability/performance of a Solid Rocket Motor (SRM) on an existing missile system without changing system form factor (Form Factor: relates to MINIMAL/NO changes in physical size, mechanical or electrical interfaces, or logistics/operations/maintenance support) . Awardees may be provided with Government Furnished Information (GFI) to ensure form factor preservation when developing their SRM technology enhancement solution. Proposers must demonstrate how their solutions minimize cost and Non-Recurring Engineering (NRE) required to integrate their SRM enhancement technology into an existing missile system. MDA highly desires a ground test demonstration of the solution to validate capability enhancement compared to an existing system. Proposers must be a small business with demonstrated expertise in the development of SRM technology. Proposers may propose a solution that is exclusive to one existing missile system or a solution that could be applied to multiple existing missile systems.

Integrate the solution developed and tested during the Phase II into an existing system to support flight testing.