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The COLD-SAT experiment for cryogenic fluid management technologyThe COLD-SAT spacecraft design experiments are described. COLD-SAT will be placed into an initial 1300 km circular orbit by an Atlas commercial launch vehicle. Electric power, experiment control and data management, attitude control, and propulsive accelarations for the experiments will be provided by the three-axis-controlled spacecraft bus. To provide data on the effects that low gravity levels might have on the heat and mass transfer processes involved, low levels of accelaration will be created. The COLD-SAT experiment will be configured into a module. The spacecraft experiment module will include three liquid hydrogen tanks; fluid transfer, pressurization and venting equipment; and instrumentation. Since the largest tank has helium-purged MLI to prevent ingress and freezing of air on the launchpad, it will contain all the liquid hydrogen at the point of launching. The hydrogen tanking system used for the Centaur upper stage of the Atlas will load and top off this tank. Atlas, with its liquid hydrogen upper stage, large payload fairing, and large launch margin, simplifies COLD-SAT design and integration.
Document ID
19910045176
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schuster, J. R.
(General Dynamics Corp. Space Systems Div., San Diego, CA, United States)
Wachter, J. P.
(Ford Aerospace Corp. Space Systems Div., Palo Alto, CA, United States)
Vento, D. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
October 1, 1990
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
91A29799
Funding Number(s)
CONTRACT_GRANT: NAS3-25062
Distribution Limits
Public
Copyright
Other

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