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.
Development of Advanced Electro-Pneumatic Actuation Systems
1972
214 pages
Report
Keine Angabe
Englisch
Hydraulic & Pneumatic Equipment , Navigation, Guidance, & Control , Pneumatic servomechanisms , Attitude control systems , Synchros , Pneumatic devices , Gases , Pneumatic valves , Feasibility studies , Surface to surface missiles , Strategic weapons , Bearings , Movable nozzles , Solid propellant rocket engines , Check valves , Dual thrust rocket engines , Guided missile components , Thrust vector control systems , Gas generating systems , Pressure , Postboost propulsion systems , Warm gas valves
Electro-Pneumatic Control Valve for EGR/ATC Actuation
Kraftfahrwesen | 1981
|Electro-Pneumatic Control Valve for EGR/ATC Actuation
SAE Technical Papers | 1981
|