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Feasibility Assessment of Thermal Barriers for RSRM Nozzle Joint LocationsSolid rockets, including the Space Shuttle solid rocket motor, are generally manufactured in large segments which are then shipped to their final destination where they are assembled. These large segments are sealed with a system of primary and secondary 0-rings to contain combustion gases inside the rocket which are at pressures of up to 900 psi and temperatures of up to 5500 F. The seals are protected from hot combustion gases by thick layers of phenolic insulation and by joint-filling compounds between these layers. Recently, though, routine inspections of nozzle-to-case joints in the Shuttle solid rocket motors during disassembly revealed erosion of the primary O-rings. Jets of hot gas leaked through gaps in the joint-filling compound between the layers of insulation and impinged on the O-rings. This is not supposed to take place, so NASA and Thiokol, the manufacturer of the rockets, initiated an investigation and found that design improvements could be made in this joint. One such improvement would involve using NASA Lewis braided thermal barriers as another level of protection for the O-ring seals against the hot combustion gases.
Document ID
20000020699
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Steinetz, Bruce M.
(NASA Glenn Research Center Cleveland, OH United States)
Dunlap, Patrick H., Jr.
(Modern Technologies Corp. Middleburg Heights, OH United States)
Date Acquired
August 19, 2013
Publication Date
July 1, 1999
Publication Information
Publication: 1998 NASA Seal/Secondary Air System Workshop
Volume: 1
Subject Category
Spacecraft Propulsion And Power
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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