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Liquid propellant thermal conditioning system test programResults are presented from more than 1500 hours of testing on a liquid hydrogen thermal conditioning unit. Test parameters included: mixer and vent flow rates; tank size; ullage volume; pressurant gas; pressurant temperature; pressure level; and heat rate. Gaseous hydrogen and helium were used as pressurants. Analytical models were developed to correlate the test data and relate the performance to that anticipated in zero gravity. Experimental and theoretical results are presented which relate the variables controlling vapor condensation at a moving interface.
Document ID
19720021137
Document Type
Contractor Report (CR)
Authors
Bullard, B. R.
(Lockheed Missiles and Space Co. Sunnyvale, CA, United States)
Date Acquired
August 6, 2013
Publication Date
July 5, 1972
Subject Category
Propellants
Report/Patent Number
NASA-CR-72971
LMSC-D159262
Funding Number(s)
CONTRACT_GRANT: NAS3-12033
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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