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Propellant development for the Advanced Solid Rocket MotorThe properties of a propellant developed for the NASA Advanced Solid Rocket Motor (ASRM) are described in terms of its composition, performance, and compliance to NASA specifications. The class 1.3 HTPB/AP/A1 propellant employs an ester plasticizer and the content of ballistic solids is set at 88 percent. Ammonia evolution is prevented by the utilization of a neutral bonding agent which allows continuous mixing. The propellant also comprises a bimodal AP blend with one ground fraction, ground AP of at least 20 microns, and ferric oxide to control the burning rate. The propellant's characteristics are discussed in terms of tradeoffs in AP particle size and the types of Al powder, bonding agent, and HTPB polymer. The size and shape of the ballistic solids affect the processability, ballistic properties, and structural properties of the propellant. The revised baseline composition is based on maximizing the robustness of in-process viscosity, structural integrity, and burning-rate tailoring range.
Document ID
19910057071
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Landers, L. C.
(Aerojet-General Corp. Sacramento, CA, United States)
Stanley, C. B.
(Aerojet Sacramento, CA, United States)
Ricks, D. W.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 91-2074
Accession Number
91A41694
Distribution Limits
Public
Copyright
Other

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