Microsatellite Propulsion Using EST Technology

This SBIR Phase I proposal is aimed at development of propulsion systems for EKV and divert. propulsion systems for low-mass interceptors that will use Vector Thrust Pulsed Detonation Rocket Engine (VTPDRE) technology. Use of PDRE will increase power density, enhance modularity, and reduce cost. Further improvements will be realized by introducing configurations with multiple PDREs and non-mechanical thrust vectoring, which wilt lead to improved engine maneuverability, reliability, and efficiency. The proposed propulsion system is based on a new engine concept that provides higher specific impulse than rockets or turbojets. It is more efficient than conventional engines because of its constant-volume, nonsteady operating cycle and has no moving parts in the power production section. In PDREs a detonation wave is initiated-in a mixture o¿ oxidizer and fuel and propagates axially in the detonation chamber. Thrust is generated when the wave impinges on the thrust wall. The use of multiple chambers allows thrust vectoring and enhances maneuverability, engine reliability, and efficiency. PDREs avoid the power density limitations of electric power generation and the low specific impulse of solid propellants. We will develop and demonstrate a low-cost propulsion system that can be used for existing systems and adapted to future advanced programs.