Variable Thrust, Multiple Start Hybrid Motor Solutions for Missile and Space Applications

Energy management in missile systems can provide substantial performance advantages, especially for modern missiles capable of all-aspect engagements. Maximum flexibility is offered by a system that can be throttled, shut off entirely and restarted when needed. The proposed project aims to achieve efficient combustion during throttling and restart capability without the need for a separate ignition system that adds to a vehicle’s mass and complexity. The innovative approach outlined in this proposal will utilize the catalytic decomposition of an oxidizer to enable flexible hybrid propulsion systems while also addressing both the low regression rate and slivering issues in hybrid rocket motors for missile or space launch applications. The Phase I effort will focus on generating conceptual designs of identified missile and upper stage propulsion systems, developing and assessing the performance and ignition characteristics of catalytic fuel grains for the oxidizers of interest, and experimentally investigating throttling capabilities and the fundamental control laws to achieve the desired thrust control. This research and development effort will be assist by the research and rocket testing facilities at Purdue University and the internal ballistics and combustion expertise at General Kinetics.