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ASRM combustion instability studiesThe objectives of this task were to measure and compare the combustion response characteristics of the selected propellant formulation for the Space Shuttle Advanced Solid Rocket Motor (ASRM) with those of the current Redesigned Solid Rocket Motor (RSRM) formulation. Tests were also carried out to characterize the combustion response of the selected propellant formulation for the ASRM igniter motor.
Document ID
19960012502
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strand, L. D. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1992
Subject Category
Inorganic And Physical Chemistry
Report/Patent Number
NAS 1.26:200170
NASA-CR-200170
NIPS-96-08134
Report Number: NAS 1.26:200170
Report Number: NASA-CR-200170
Report Number: NIPS-96-08134
Meeting Information
Meeting: NATO Advisory Group for Aerospace Research and Development
Location: Milan
Country: Italy
Start Date: October 23, 1995
End Date: October 27, 1995
Accession Number
96N18739
Funding Number(s)
CONTRACT_GRANT: NAS7-918
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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