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.


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    Title :

    Production Quality Assurance Testing of a Thiokol Minuteman LGM-30G Stage III Rocket Motor at Simulated Pressure Altitude, Motor PQA-102


    Contributors:
    D. E. Franklin (author) / C. H. Kunz (author)

    Publication date :

    1973


    Size :

    64 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English