ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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-seclbm. The roll control subsystem structural integrity was satisfactory.
Prepared in cooperation with ARO, Inc., Tullahoma, Tenn., Rept. no. ARO-ETF-TR-73-19.