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Flight motor set 360L002 (STS-27R). Volume 5: Nozzle componentA review of the performance and post-flight condition of the STS-27 Redesigned Solid Rocket Motor (RSRM) nozzles is presented. Thermal/Structural instrumentation data is reviewed, and applicable Discrepancy Reports (DRs) and Process Departures (PDs) are presented. The Nozzle Component Program Team (NCPT) performance evaluation and the Redesign Program Review Board (RPRB) assessment is included. The STS-27 nozzle assemblies were flown on the RSRM Second Flight (Space Shuttle Atlantis) on 2 December 1988. The nozzles were a partially submerged convergent and/or divergent movable design with an aft pivot point flexible bearing. The nozzle assemblies incorporated the following features: RSRM forward exit cone with snubber assembly, RSRM fixed housing, Structural backup Outer Boot Ring (OBR), RSRM cowl ring, RSRM nose inlet assembly, RSRM throat assembly, RSRM aft exit cone assembly with Linear-Shaped Charge (LSC), RTV backfill in Joints 1, 3, and 4, Use of EA913 NA adhesive in place of EA913 adhesive, Redesigned nozzle plug, and Carbon Cloth Phenolic (CCP) with 750 ppm sodium content. The CCP material usage for the STS-27 forward nozzle and aft exit cone assemblies is shown.
Document ID
19900012495
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Meyer, S. A. (Thiokol Corp. Brigham City, UT, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-183945
NAS 1.26:183945
TWR-17541-5
Accession Number
90N21811
Funding Number(s)
CONTRACT_GRANT: NAS8-30490
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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