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Thermal performance of an integrated thermal protection system for long-term storage of cryogenic propellants in spaceIt was demonstrated that cryogenic propellants can be stored unvented in space long enough to accomplish a Saturn orbiter mission after 1,200-day coast. The thermal design of a hydrogen-fluorine rocket stage was carried out, and the hydrogen tank, its support structure, and thermal protection system were tested in a vacuum chamber. Heat transfer rates of approximately 23 W were measured in tests to simulate the near-Earth portion of the mission. Tests to simulate the majority of the time the vehicle would be in deep space and sun-oriented resulted in a heat transfer rate of 0.11 W.
Document ID
19770017239
Document Type
Other - NASA Technical Note (TN)
Authors
Dewitt, R. L.
(NASA Lewis Research Center Cleveland, OH, United States)
Boyle, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1977
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TN-D-8320
E-8881
Accession Number
77N24183
Funding Number(s)
PROJECT: RTOP 506-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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