ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
An LGM-30G Stage III Solid-propellant rocket motor, PQA-103, was fired in Rocket Development Test Cell J-5, Engine Test Facility ETF, in support of the Minuteman Stage III Production Quality Assurance Test Program. Motor ballistic, liquid-injection thrust vector control system, roll control system, 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 squibs was accomplished, as programmed, 2.5 sec before motor ignition at a pressure altitude of 102,000 ft. The motor was ignited at a pressure altitude of 101,000 ft. Motor ignition delay time was 89 msec. Motor thrust termination occurred at 59.93 sec at a chamber pressure of 75.3 psia. During the 59.93-sec action time the motor produced an unaugmented vacuum total impulse of 2,083,103 lbf-sec. The unaugmented vacuum specific impulse was 284.96 lbf-seclbm. Maximum interstage pressure at thrust termination was within specificaton. Postfire motor structural integrity was satisfactory.
Prepared in cooperation with ARO, Inc., Tullahoma, Tenn., Rept. no. ARO-ETF-TR-73-35. DOI: 10.21236/AD0909985