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Evidence of erosive burning in shuttle solid rocket motorKnown models of Shuttle Solid Rocket Motor (SRM) performance have failed to produce pressure-time traces which accurately matched actual motor performance, especially during the first 5 seconds after ignition and during the last quarter of web burn time. Efforts to compensate for these differences in model reconstruction and actual performance resulted in resorting to the use of a Burning Anomaly Rate Function (BARF). It was suspected that propellant erosive burning was primarily responsible for the variation of model from actual results. The three dimensional Hercules Grain Design and Internal Ballistics Evaluation Program was made operational and slightly modified and an extensive trial and error effort was begun to test the hypothesis of erosive burning as an explanation of the burning anomaly. It was found that introduction of erosive burning (using Green's erosive burning equation) over portions of the aft segment grain and above a threshold gas Mach number did, in fact, give excellent agreement with the actual motor trace.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Martin, C. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 11, 2013
Publication Date
February 1, 1983
Publication Information
Publication: APL The 1983 JANNAF Propulsion Meeting, Vol. 1
Subject Category
Spacecraft Propulsion And Power
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.

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