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Space Shuttle SRM Ignition SystemThis paper presents the Space Shuttle SRM Ignition System, which consists of a large solid propellant main igniter, a small solid propellant initiating igniter and an electromechanical safety and arming device containing two NASA Standard Initiators and a B-KNO3 pyrotechnic booster charge. In development motors, the igniter also has a valve through which CO2 is injected for post-firing quench of the SRM. The igniter has redundant, testable seals at all pressurized joints and three major reusable components; the case, the adapter, and the S&A device. Two development problem areas are discussed. One problem area was transverse mode combustion instability in the main igniter with maximum amplitude of 340 psi peak-to-peak at a frequency of 1500 Hz, which was reduced by a propellant grain configuration change and a change from a 2% aluminum content propellant to a formulation containing 10% aluminum. The other problem area was an excessively rapid rise of thrust in the SRM, which was reduced by reducing the igniter mass flow rate. This mass flow rate reduction was accomplished by removing portions of the grain starpoints in the head end.
Document ID
19780059629
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bolieau, C. W.
(Thiokol Corp. Brigham City, UT, United States)
Baker, J. S.
(Thiokol Corp. Brigham City, UT, United States)
Folkman, S. L.
(Thiokol Corp. Brigham City, Utah, United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 78-987
Meeting Information
Meeting: Joint Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: July 25, 1978
End Date: July 27, 1978
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
78A43538
Funding Number(s)
CONTRACT_GRANT: NAS8-30490
Distribution Limits
Public
Copyright
Other

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