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Heat pipe technology for advanced rocket thrust chambersThe application of heat pipe technology to the design of rocket engine thrust chambers is discussed. Subjects presented are: (1) evaporator wick development, (2) specific heat pipe designs and test results, (3) injector design, fabrication, and cold flow testing, and (4) preliminary thrust chamber design.
Document ID
19720026294
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Rousar, D. C. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 2, 2013
Publication Date
September 15, 1971
Subject Category
Thermodynamics And Combustion
Report/Patent Number
REPT-697-F
NASA-CR-128320
Report Number: REPT-697-F
Report Number: NASA-CR-128320
Accession Number
72N33944
Funding Number(s)
CONTRACT_GRANT: NAS7-697
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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