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Orbit Transfer Vehicle Engine Study. Phase A, extension 1: Advanced expander cycle engine optimizationThe performance optimization of expander cycle engines at vacuum thrust levels of 10K, 15K, and 20K lb is discussed. The optimization is conducted for a maximum engine length with an extendible nozzle in the retracted position of 60 inches and an engine mixture ratio of 6.0:1. The thrust chamber geometry and cycle analyses are documented. In addition, the sensitivity of a recommended baseline expander cycle to component performance variations is determined and chilldown/start propellant consumptions are estimated.
Document ID
19810013551
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Mellish, J. A. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1979
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
REPT-3299-E1-T1
NASA-CR-161710
Accession Number
81N22081
Funding Number(s)
CONTRACT_GRANT: NAS8-32999
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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