Space Propulsion Group, Inc (SPG) proposes to conduct investigations on ignition and barrier systems for multi-pulse rocket motors. The benefits of the proposed work is the reliable ignition of propellant grains under various free chamber volume conditions and the ability to terminate thrust generation for a desired amount of time following discrete propellant grain burnout. Capability to operate with multiple thrust pulses without the complexity of staging is beneficial for reducing propulsion system costs and increasing mission flexibility. The ability to terminate propulsive thrust following propellant grain combustion relies on the ability to physically and thermally isolate the discrete propellant grains. The significantly different chamber conditions at the start of each of the individual pulses require a separate approach for ignition. An ignition system that can be tailored to the initial conditions of each propellant grain allows great flexibility in selecting mission profiles. The Phase I work considers the development of the igniter system for discrete pulses and a pulse separation device. Evaluation and design of potential igniter systems as well as design and preliminary testing of the pulse separation device will be conducted.
Keywords: Pulse Separation Device, Pulse Separation Device, Solid Rocket Motors, Dual-Pulse Motor, Propellant Ignition
