A Theoretical Study of Space Equivalent Thermal Conditions and Their Applicability
Report Number: AMRL TDR 64-20
Author(s): Auxier, T. A.
Corporate Author(s): University of Kentucky Research Foundation
Laboratory: Biomedical Laboratory
Date of Publication: 1964-03
Pages: 114
Contract: AF 33(657)-11346
DoD Project: 7164
DoD Task: 716409
Identifier: AD0437575
Abstract:
Radiation heat transfer calculations are made for a cylindrical model of a 50th percentile suited space man in 7 space configurations: (1) deep space probe, (2) a point 136 miles from the bright side of the moon, (3) a point 136 miles from the surface of the dark side of the moon, (4) a point 500 miles from the surface of the bright side of the earth, (5) a point 500 miles form the surface of the dark side of the earth, (6) a 500 mile circular earth orbit a5d (7) a 136 mile circular moon orbit. Similarly, radiation heat transfer calculations are made for the same space man model in four hypothetical chamber configurations I, II, III and IV. The space results are superimposed on the chamber results in order to determine equivalent temperatures for simulating the given space conditions. For instance, depending on the space suit absorptance, the required chamber III temperature for simulating the deep space probe can vary from 260 to 1150R. With these results the capabilities of the AMRL thermal chamber for simulating any one of the seven space configurations are determined.
Provenance: RAF Centre of Aviation Medicine
Author(s): Auxier, T. A.
Corporate Author(s): University of Kentucky Research Foundation
Laboratory: Biomedical Laboratory
Date of Publication: 1964-03
Pages: 114
Contract: AF 33(657)-11346
DoD Project: 7164
DoD Task: 716409
Identifier: AD0437575
Abstract:
Radiation heat transfer calculations are made for a cylindrical model of a 50th percentile suited space man in 7 space configurations: (1) deep space probe, (2) a point 136 miles from the bright side of the moon, (3) a point 136 miles from the surface of the dark side of the moon, (4) a point 500 miles from the surface of the bright side of the earth, (5) a point 500 miles form the surface of the dark side of the earth, (6) a 500 mile circular earth orbit a5d (7) a 136 mile circular moon orbit. Similarly, radiation heat transfer calculations are made for the same space man model in four hypothetical chamber configurations I, II, III and IV. The space results are superimposed on the chamber results in order to determine equivalent temperatures for simulating the given space conditions. For instance, depending on the space suit absorptance, the required chamber III temperature for simulating the deep space probe can vary from 260 to 1150R. With these results the capabilities of the AMRL thermal chamber for simulating any one of the seven space configurations are determined.
Provenance: RAF Centre of Aviation Medicine