Aging and Surveillance Testing of an Aerojet Minuteman LGM-30G Stage III Rocket Motor at Simulated Pressure Altitude (Motor S/N TMS-10).

摘要

An LGM-30G Stage III solid-propellant rocket motor, designated TMS-10 (aged 42 months), was fired in Rocket Development Test Cell (J-5), Engine Test Facility (ETF), in support of the Minuteman III Stage III Aging and Surveillance (A and S) Test Program on March 8, 1973. There was an apparent insulator/grain separation 10 sec after motor ignition as indicated by chamber pressure and linear potentiometers located on the motor aft dome and nozzle mounting flange. Vacuum thrust attainted upper specification limits from 18 to 28 sec after motor ignition and was below specification limits from 46 to 54 sec. Motor ballistic, liquid-injection thrust vector control system, roll control, and thrust termination system performance was within model specification requirements. Ignition of the roll control gas generator and the liquid-injection thrust vector control isolation valve squibs was accomplished, as programmed, 2.5 sec before motor ignition at a pressure altitude of 100,000 ft. The motor was ignited at a pressure altitude of 100,000 ft. Motor ignition delay time was 90 msec. Motor thrust termination occurred at 60.49 sec at a chamber pressure of 74.3 psia. The motor produced an unaugmented vacuum total impulse of 2,083,900 lbf-sec during action time. The unaugmented vacuum specific impulse was 284.01 lbf-sec/lbm. (Author)