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Thermal Vacuum Chamber Shroud Performance With Gaseous Nitrogen CoolingThe results are presented for calculations of shroud surface temperature for various flow rates of gaseous nitrogen through the liquid nitrogen shrouds of a large thermal vacuum chamber. The conditions imposed provide conservative bounds for Mars surface simulation inside the chamber during thermal testing of an appropriate test object. It is shown that the shroud surfaces seen by the object can be held within an acceptable temperature range by providing a reasonable flow of gaseous nitrogen to the shrouds at a reasonable pressure, and that no change to the present shroud system need be made which would affect its suitability for liquid nitrogen cooling.
Document ID
19720014634
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
R A Farmer
(Martin Marietta Corp. Denver, CO, United States)
Date Acquired
August 6, 2013
Publication Date
May 1, 1972
Publication Information
Publication: Proceedings of the Sixth Space Simulation Symposium
Publisher: National Aeronautics and Space Administration
Subject Category
Facilities, Research, And Support
Meeting Information
Meeting: 6th Space Simulation Symposium
Location: New York, NY
Country: US
Start Date: May 1, 1972
End Date: May 3, 1972
Sponsors: American Astronautical Society and American Institute of Aeronautics and Astronautics, National Aeronautics and Space Administration, American Society For Testing and Materials, Institute of Environmental Sciences
Accession Number
72N22284
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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