Advanced Composite Propellant Replacement for High Performance Plateau Bruning Double Base Navy SBIR FY2013.2 Sol No.: Navy SBIR FY2013.2 Topic No.: N132-105 Topic Title: Advanced Composite Propellant Replacement for High Performance Plateau Bruning Double Base Proposal No.: N132-105-0555 Firm: Physical Sciences Inc. 20 New England Business Center Andover, Massachusetts 01810-1077 Contact: Justin Sabourin Phone: (978) 689-0003 Web Site: http://www.psicorp.com Abstract: Physical Sciences Inc. proposes to develop and demonstrate novel composite propellant formulations using chemically modified forms of currently used propellant ingredients. The developed formulations will allow drop-in replacement of presently used double base formulations used CAD/PADs, such as rocket motor ejection seats. The innovative chemistries, combined with specific changes in the propellant formulations, will enable plateau burning rate profiles up to 5000 psi, with fast burning rates and minimum temperature sensitivity. The chemical modifications will maintain or improve the ignition sensitivity of the propellant. The proposed concept permits the inclusion of these simple, low cost chemistries under safe operations, and will not require alterations to current propellant manufacturing procedures. In Phase I, the proposed investigation will focus on defining specific performance metrics of the replacement propellant, the development of critical chemical synthesis procedures, and characterizing the effects of the chemical modifications. Phase II will refine required performance metrics through detailed modeling, upgrade formulations to meet requirements, identify new applications, as well as scale-up chemical synthesis operations. We envision these chemical modifications to create a new class of propellant with increased performance, low cost, and reduced sensitivity to unintended ignition threats. Benefits: The proposed propellant formulation will enhance high pressure burning rate properties, and improve sensitivity and IM performance in comparison to standard ammonium perchlorate based composite propellants. This will enable composite propellants to provide better propulsive performance in high pressure rocket motors, such as boosters used in multistage applications, tactical missiles, and CAD/PADs. This technology will be of interest throughout the DoD, NASA, and the commercial space launch industry. Patented technologies developed will also be of potential benefit to the JIMTP (Joint Insensitive Munitions Technology Program) due to the improved reaction response of composite propellant munitions to unintended ignition threats such as slow-cook off and high energy impacts. Return