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Propulsion system tests on a full scale Centaur vehicle to investigate 3-burn mission capability of the D-lT configurationPropulsion system tests were conducted on a full scale Centaur vehicle to investigate system capability of the proposed D-lT configuration for a three-burn mission. This particular mission profile requires that the engines be capable of restarting and firing for a final maneuver after a 5-1/2-hour coast to synchronous orbit. The thermal conditioning requirements of the engine and propellant feed system components for engine start under these conditions were investigated. Performance data were also obtained on the D-lT type computer controlled propellant tank pressurization system. The test results demonstrated that the RL-10 engines on the Centaur vehicle could be started and run reliably after being thermally conditioned to predicted engine start conditions for a one, two and three burn mission. Investigation of the thermal margins also indicated that engine starts could be accomplished at the maximum predicted component temperature conditions with prestart durations less than planned for flight.
Document ID
19740011284
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Groesbeck, W. A. (NASA Lewis Research Center Cleveland, OH, United States)
Baud, K. M. (NASA Lewis Research Center Cleveland, OH, United States)
Lacovic, R. F. (NASA Lewis Research Center Cleveland, OH, United States)
Tabata, W. K. (NASA Lewis Research Center Cleveland, OH, United States)
Szabo, S. V., Jr. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
February 5, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-71511
E-7889
Accession Number
74N19397
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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