Development of Advanced Electro-Pneumatic Actuation Systems.

摘要

The feasibility of warm-gas pneumatic controls was demonstrated for three different applications for intercontinental ballistic missiles by the development of the following components: (1)actuators (two sizes), one for flexible bearing sealed movable nozzle and one for a fluid bearing sealed movable nozzle for large solid propellant rocket motors: (2) interchamber control valve for a flightweight dual chamber solid rocket motor post-boost propulsion system; (3)actuator for flexible bearing sealed movable nozzle for a flightweight dual chamber solid rocket motor post-boost propulsion system. The above components were designed, subjected to engineering development tests and then proven in warm-gas demonstration tests. Test results indicate that the warm-gas approach is feasible and should be considered in future missile control systems.