Highly Reliable, Reusable, Non-Toxic Rocket Engine Ignition Systems

Development of an existing microwave generated plasma igniter including a detailed computational modeling effort is proposed. This igniter generates a continuous high temperature oxygen plasma and offers a non-toxic approach to rocket ignition using LOX oxidixer with either kerosene, methane and hydrogen fuels. The proposed development effort will focus on experimentally demonstrating the highly operable, highly reusable, and highly reliable features already inherent in the fundamental igniter design. Modeling and simulation efforts relating to this igniter will be directed toward predicting ignition and flame spreading characteristics applicable to future Air Force booster and upper stage engines.