Results from a continuing, time-accurate computational study of the combustion gas flow inside the Space Shuttle Redesigned Solid Rocket Motor (RSRM) are presented. These computational fluid dynamic (CFD) analyses duplicate unsteady flow effects which interact in the RSRM to produce pressure oscillations, and resulting thrust oscillations, at nominally 15, 30, and 45 Hz. Results of the Navier-Stokes computations made at mean pressure and flow conditions corresponding to 80 seconds after motor ignition both with and without a protruding, rigid inhibitor at the forward joint cavity are presented here.
A comparative study of the effects of inhibitor stub length on solid rocket motor combustion chamber pressure oscillations: RSRM at T = 80 seconds, preliminary results
01.07.1992
Aufsatz (Konferenz)
Keine Angabe
Englisch
RSRM Chamber Pressure Oscillations: Transit Time Models and Unsteady CFD
British Library Conference Proceedings | 1996
|Solid Rocket Motor Combustion Chamber Aeroacoustics
AIAA | 1978
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