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Effect of subcooling on the on-orbit pressurization rate of cryogenic propellant tankageThe SOLA-ECLIPSE code is being developed to enable prediction of the behavior of cryogenic propellants in spacecraft tankage. A brief description of the formulations used for modeling heat transfer and for determining thermodynamic state is presented. Code performance is verified through comparison to experimental data for the self-pressurization of scale model liquid hydrogen tanks. SOLA-ECLIPSE is used to examine the effect of initial subcooling of the liquid phase on the self-pressurization rate of an on-orbit full scale liquid hydrogen tank typical for a chemical propulsion Orbital Transfer Vehicle. The computational predictions show that even small amounts of subcooling will significantly decrease the self-pressurization rate. Further, if the cooling is provided by a Thermodynamic Vent System, it is concluded that small levels of subcooling will maximize propellant conservation.
Document ID
19860055139
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hochstein, J. I.
(NASA Lewis Research Center Cleveland, OH, United States)
Ji, H.-C.
(Washington University St. Louis, MO, United States)
Aydelott, J. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 86-1253
Accession Number
86A39877
Funding Number(s)
CONTRACT_GRANT: NAG3-578
Distribution Limits
Public
Copyright
Other

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