Temperature-Insensitive Composite Propellants with Tunable Plateau Burning Using In-Situ Energetic Nanoparticles Navy SBIR FY2013.2 Sol No.: Navy SBIR FY2013.2 Topic No.: N132-105 Topic Title: Temperature-Insensitive Composite Propellants with Tunable Plateau Burning Using In-Situ Energetic Nanoparticles Proposal No.: N132-105-1272 Firm: Helicon Chemical Company LLC 12001 Avalon Lake Dr., #304 Orlando, Florida 32828 Contact: David Reid Phone: (321) 300-6266 Abstract: The objective of this Phase I proposal is to demonstrate the feasibility of using a combination of chemical and nanoparticle additives to produce high-performance, temperature-insensitive composite solid propellants with plateau burning rates greater than 1 in/s at 2000 psi for use in Navy aircraft ejection seat systems. The key innovation in this work is the combinations of novel additives and processing methods which provide enhanced controllability of composite propellant burning rates. Specifically, a chemical additive is used to produce plateau and negative pressure dependence, and a unique in-situ chemical process forms aluminum nanoparticles directly in the propellant binder, which increases performance. Feasibility will be determined by burning rate, temperature dependence, safety, and mechanical property tests showing that this propellant meets Navy's requirements as an alternative to current double-base propellants in this application. Benefits: This technology will produce propellants with improved temperature insensitivity, increased performance, and better burning-rate control than existing composite propellant formulations. The plateau burning rates will be tailored to be comparable to the double-base propellants currently used in aircraft pilot ejection systems. The composite propellant formulation will be more resistant to temperature degradation. and will be designed to meet DoD insensitive munitions requirements. The improved propellant safety will benefit the DoD-wide need for high-performance insensitive munitions compliant propellants. The high performance (burning rate and specific impulse) will benefit SDACS and boost applications for interceptors and other missiles. The technology can also be applied to liquid propellants and fuels, for potential applications in government and commercial space launch vehicles for improved payload capability, and military aviation applications for reduced fuel consumption and time to target. Return