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A comparative study of the effects of inhibitor stub length on solid rocket motor combustion chamber pressure oscillations: RSRM at T = 80 seconds, preliminary resultsResults 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.
Document ID
19920023004
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chasman, D. (Rockwell International Corp. Huntsville, AL., United States)
Burnette, D. (Rockwell International Corp. Huntsville, AL., United States)
Holt, J. (Rockwell International Corp. Huntsville, AL., United States)
Farr, R. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1992
Publication Information
Publication: NASA. Goddard Space Flight Center, Tenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion, Part 2
Subject Category
Spacecraft Propulsion And Power
Accession Number
92N32248
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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