An LGM-30G Stage III solid-propellant rocket motor, PQA-102, was fired in Rocket Development Test Cell (J-5), Engine Test Facility (ETF). The roll control subsystem was independently tested off-motor. Motor ballistic, roll control system, thrust vector control, and thrust termination system performance was within model specification requirements. The motor was ignited at a pressure altitude of 102,000 ft. Motor ignition delay time was 86 msec. Motor thrust termination occurred at 60.18 sec at a chamber pressure of 75.3 psia. Motor action time was 60.18 during which the motor produced an unaugmented vacuum total impulse of 2,083,534 lbf-sec. The unaugmented vacuum specific impulse was 284.94 lbf-sec/lbm. The roll control subsystem structural integrity was satisfactory.
Production Quality Assurance Testing of a Thiokol Minuteman LGM-30G Stage III Rocket Motor at Simulated Pressure Altitude, Motor PQA-102
1973
64 pages
Report
No indication
English
Rocket Engines & Motors , Missile Technology , Third stage engines , Surface to surface missiles , Captive tests , Solid propellant rocket engines , Starting , Ignition , High altitude , Barometric pressure , Simulation , Time , Thrust , Thrust vector control systems , Thrust termination systems , Specific impulse , Roll , Flight control systems , Combustion chambers , Pressure , Quality control , Performance(Engineering) , Minuteman , Minuteman 3 missiles