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Space shuttle orbit maneuvering engine reusable thrust chamber. Task 10: Data dump comparison of 8- and 10- inch diameter thrust chambersAn analytical and design study was conducted to compare the high and low contraction ratio thrust chambers for regenratively cooled orbit maneuvering engines for the space shuttle was conducted. The design concepts were evaluated on the basis of weight, pressure drop, and performance. Only the basic thrust chamber assembly was considered. The assembly consists of the injector, the regeneratively cooled thrust chamber, and the radiation cooled nozzle. A two dimensional thermal analysis of the channel section is provided.
Document ID
19750010240
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Pauckert, R. P. (Rockwell International Corp. Canoga Park, CA, United States)
Tobin, R. D. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1975
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
ASR-75-37
NASA-CR-141675
Accession Number
75N18312
Funding Number(s)
CONTRACT_GRANT: NAS9-12802
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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