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Cryopump for large pulses of hydrogenA test involving a flow of hot hydrazine decomposition products at a rate of 13.6 g/s (0.03 lb/s) established the requirement to maintain pressure in an 11.9-m-(39 ft) diameter space chamber below 200 microns. The flow, 2/3 hydrogen and 1/3 nitrogen by volume, continued for several periods ranging from 3 to 15 min. The pressure requirement was necessary to minimize thermal effects of the gas on the test vehicle but was well beyond the capability of the existing facility pumps. Various methods of obtaining additional temporary jump capacity were considered. From these, the slugged-charcoal approach was selected as the quickest and least expensive method to implement.
Document ID
19820017421
Document Type
Conference Paper
Authors
Moore, B. C. (McDonnell-Douglas Astronautics Co. Saint Louis, MO, United States)
Camarillo, R. G. (McDonnell-Douglas Astronautics Co. Saint Louis, MO, United States)
Morrow, J. T. (McDonnell-Douglas Astronautics Co. Saint Louis, MO, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Publication Information
Publication: NASA. Goddard Space Flight Center 12th Space Simulation Conf.
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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