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RSRM-13 (360Q013) ballistics mass properties flight designation STS-41The propulsion performance and reconstructed mass properties data from Thiokol's RSRM-13 motors which were assigned to the STS-41 launch are presented. The SRM propellant, TP-H1148, is a composite type solid propellant, formulated of polybutadiene acrylic acid acryonitrile terpolymer binder, epoxy curing agent, ammonium perchlorate oxidizer, and aluminum powder fuel. A small amount of burning rate catalyst (iron oxide) was added to achieve the desired propellant burn rate. The propellant evaluation and raw material information are also presented. The presented ballistic performance was based on the Operational Flight Instrumentation. The adjustments made to the raw data on this flight include biasing the data to correct ambient pressure before liftoff. The performance from each motor as well as matched pair performance values were well within the CEI Specification requirements.
Document ID
19910007826
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Laubacher, Brian A.
(Thiokol Corp. Brigham City, UT, United States)
Richards, M. C.
(Thiokol Corp. Brigham City, UT, United States)
Date Acquired
September 6, 2013
Publication Date
December 11, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-184092
TWR-17552-10
NAS 1.26:184092
Accession Number
91N17139
Funding Number(s)
CONTRACT_GRANT: NAS8-30490
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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