LGM-30G Stage II solid-propellant rocket motor (S/N PQA6-60) was fired in Rocket Development Test Cell (J-5), Engine Test Facility (ETF) on November 27, 1972, in support of the Minuteman Production Quality Assurance Test Program. Motor ballistic, liquid-injection thrust vector control system, and roll control system performances were within model specification requirements. Ignition of both the roll control and the liquid-injection thrust vector gas generators was accomplished as programmed, 3.7 sec before motor ignition at a pressure altitude of 102,000 ft. The motor was ignited at a pressure altitude of 96,000 ft. Motor ignition delay time was 109 msec. Motor action time was 64.25 sec, during which the motor produced an unaugmented vacuum total impulse of 3,950,581 lbf-sec. The unaugmented vacuum specific impulse was 287.54 lbf-sec/lbm. The liquid-injection thrust vector control and roll control systems operated as programmed throughout the firing. Postfire motor structural integrity was satisfactory with the exception that the nozzle sea-level liner had been ejected during the firing at T + 63.9 sec. (Author)
Production Quality Assurance Testing of a Minuteman III LGM-30G Stage II Rocket Motor at Simulated Pressure Altitude (Motor S/N PQA6-60)
1973
68 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Second-stage motors , Solid propellant rocket engines , Captive tests , Surface to surface missiles , Pressure , Altitude , Simulation , Secondary injection , Thrust vector control systems , Liquids , Fluorohydrocarbons , Gas generator engines , Ignition , Specific impulse , Thrust , Roll , Rocket nozzles , Performance(Engineering) , Nozzle inserts , Quality control , Sr-19 motors , Minuteman , Minuteman 3 missiles , M-56 motors , Sr-19-aj-1 motors