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Ignition overpressure study from solid rocket motor firingsThe objective was to investigate, through experimental means, the basic mechanisms influencing ignition overpressure and to determine ways to suppress ignition overpressure. Ignition overpressure was studied using solid rocket motors with geometry scaled at 1 percent of the Shuttle's Solid Rocket Boosters. Both water injection and aerosol foam were examined as a mean of reducing ignition overpressure. The results of the water injection tests indicate that a relatively small amount of water is sufficient to provide significant suppression. Of the flow rates tested, the lower water injection flow rates provided the best reduction of the ignition overpressure wave. Also, the test results show there is an optimum water flow rate range that provides the best suppression, and as this range is exceeded the effectiveness of water to reduce ignition overpressure is decreased. Aerosol foam provided very little reduction of ignition overpressure, but only small volumes of foam were used and further testing is necessary to determine its total effectiveness as a means of suppression.
Document ID
19870009174
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Counter, Douglas D. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1987
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-86587
NAS 1.15:86587
Accession Number
87N18607
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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