Two Aerojet SVM-6 (S/N Q2 and Q3) solid-propellant rocket motors were fired at ignition pressure altitudes of 113,000 and 123,000 ft while spinning about the axial centerline at 110 rpm. The firings were accomplished as part of the SVM-6 Qualification Test Program. Motor S/N Q2 was preconditioned to a temperature of 110 F prior to firing, and motor S/N Q3 was preconditioned to a temperature of 10 F prior to firing. The primary objective was to demonstrate compliance with motor specifications. Vacuum ballistic performance, altitude ignition characteristics, motor temperature time-history, structural integrity of the motor, and the lateral (nonaxial) component of the thrust vector are presented and discussed. (Author)
Altitude Qualification Test of the Aerojet SVM-6 Solid-Propellant Rocket Motor
1975
45 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Solid propellant rocket engines , Communication satellites , Performance(Engineering) , Orbits , High altitude , Ignition , High temperature , Low temperature , Vacuum , Ballistic testing , Thrust vector control systems , Thrust , Specific impulse , Burning rate , Rocket propellant grains , Polybutadiene , SVM-6 rocket motors , NATO 3 satellite
The history of solid rocket propulsion and Aerojet
AIAA | 1999
|NTRS | 1973
|NTIS | 1971
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