The Aerojet Solid Propulsion Company modified, full-scale, heavyweight, controllable solid rocket motor (CSRM-4), was successfully test fired at simulated pressure altitude in Rocket Development test cell J-5 of the engine test facility, AEDC, on June 25, 1973. The primary test objective, propellant extinguishment, was demonstrated on five repetitive programmed firings; The five 5-sec duration firings were separated by 60-sec extinguished coast periods. Motor chamber pressure at propellant extinguishment was 36, 26, 32, 30, and 26 psia for the five firings. Postfire condition of the motor was satisfactory. (Author).
Altitude Test of the Aerojet Modified Heavyweight Full-Scale Controllable Solid-Propellant Rocket Motor (CSRM-4)
1973
58 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Controllable thrust rocket engines , Solid propellant rocket engines , Performance(Engineering) , Captive tests , Variable area nozzles , Rocket nozzles , Rocket propellant grains , Combustion chambers , Pressure , Pintles , Nozzles , Servomechanisms , Control , Extinguishing , High altitude , Simulation , ANP-3357-4B propellant , Restartable rocket motors
The history of solid rocket propulsion and Aerojet
AIAA | 1999
|NTRS | 1973
|NTIS | 1973
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