DEVELOPMENT OF A HIGH-TEMPERATURE NUCLEAR-RADIATION-RESISTANT PNEUMATIC POWER SYSTEM FOR FLIGHT VEHICLES

摘要

A revised system approach is presented using a 750/1, 500-psi closed pneumatic system in place of the original 500/2, 000~psi pneumatic system.nThe rotary actuator and servo package (RASP) volume chamber was repaired successfully and was followed by proof pressure internal leakage, external leak¬age, null pressure and threshold tests in addition to preliminary cycling of the unit. Although internal leakage, null pressure and threshold slightly exceeded specification requirements, experimental testing is continuing. A fourth high-temperature (1, 500° F) run was accomplished on the pilot portion of the Model X pressure regulator. In addition, a modified pneumatic filter was received from Bendix during this reporting period. Due to the redirection of effort, further testing of the relief valve was suspended.