Development and Demonstration of an On-Command, Variable Thrust, Axial Pintle System for Tactical Rocket Motors

In this Phase I program, ISP, Inc. proposes to design, develop, and deliver a low cost hot gas valve to MICOM for testing in their advanced tactical missile propulsion program. The proposed valve is designed to provide continuous throttling of 2000 degrees F. fuel-rich solid propellant gas over a mass flow ratio of 5:1 with a maximum flow rate of 1 lbm/sec. The valve design is based on the axially translating pintle which controls flow by varying nozzle throat ara. To achieve the desired low cost, the valve comprises commercially-available control components such as the actuator and the servovalve and features a unique hydraulic power supply that derives its power from gas generator chamber pressure. The concept is scaleable over the desired 0.1 to 50 lbm/sec mass flow rate range and is compatible with conventional nozzle materials as evidenced by previous pintle nozzle development which has demonstrated a flow rate range of less than 0.1 to over 1000 lbm/sec and gas temperatures up to 6000 degrees F. ISP, Inc. is proposing a six-month program at the conclusion of which a heavyweight hot gas valve will be delivered to MICOM with sufficient spare parts to support a minimum of five advanced propulsion tests. Prior to delivery, ISP, Inc. will verify valve survivability and operability with a fullscale hot fire test.