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Advanced oxygen-hydrocarbon rocket engine studyThe program consists of parametric analysis and design to provide a consistent engine system data base for defining advantages and disadvantages, system performance and operating limits, engine parametric data, and technology requirements for candidate high pressure LO2/Hydrocarbon engine systems. The parametric chamber and nozzle cooling analysis was completed for the four potential coolants: RP-1, LCH4, LO2, and LH2. A summary of the cooling capability of each propellant is presented.
Document ID
19810014651
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Obrien, J. O. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Ewen, R. L. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Kent, S. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Meagher, G. M. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 4, 2013
Publication Date
April 10, 1980
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
REPT-33452-M-3
NASA-CR-161760
Report Number: REPT-33452-M-3
Report Number: NASA-CR-161760
Accession Number
81N23184
Funding Number(s)
CONTRACT_GRANT: NAS8-33452
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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