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Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 3B: High pressure fuel turbo-pump preburner pump bearing assembly analysisThe analysis performed on the High Pressure Oxidizer Turbopump (HPOTP) preburner pump bearing assembly located on the Space Shuttle Main Engine (SSME) is summarized. An ANSYS finite element model for the inlet assembly was built and executed. Thermal and static analyses were performed.
Document ID
19890018324
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Power, Gloria B. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Violett, Rebeca S. (Lockheed Missiles and Space Co. Huntsville, AL, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-183666
NAS 1.26:183666
LMSC-HEC-TR-F268584-VOL-3B
Report Number: NASA-CR-183666
Report Number: NAS 1.26:183666
Report Number: LMSC-HEC-TR-F268584-VOL-3B
Accession Number
89N27695
Funding Number(s)
CONTRACT_GRANT: NAS8-37282
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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