Techniques And Materials For Passive Thermal Control Of Rigid And Flexible Extravehicular Space Enclosures

Item

Title
Techniques And Materials For Passive Thermal Control Of Rigid And Flexible Extravehicular Space Enclosures
Date
1967
Index Abstract
Not Available
Photo Quality
Complete
Report Number
AMRL TR 67-128
Creator
Richardson, David L.
Corporate Author
Little (Arthur D) Inc Cambridge Mass
Laboratory
Aerospace Medical Research Laboratories
Date Issued
1967-12-01
Extent
120
Identifier
AD0666940
Access Rights
Distribution of this document is unlimited. It may be released to the Clearinghouse, Department of Commerce, for sale to the general public.
Distribution Classification
1
Contract
AF 33(615)-3533
DoD Project
7164
DoD Task
716412
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Distribution Conflict
No
Abstract
The results of the analysis indicate that when an astronaut in a flexible enclosure (soft space suit) works on the surface of a large spacecraft, the temperatures on his external surface are markedly increased over those which occur when he is not near the spacecraft. Moreover, passive thermal control of the astronaut is not possible when he is near the spacecraft. The techniques investigated for thermally coupling an astronaut with his thermal control system include liquid cooled undergarments, gas cooling, and heat transfer to the cooled walls of his enclosure. Techniques were investigated for increasing the conductance through soft space suit insulations by compressing the insulation. The insulation of a cylindrical section of a space suit arm was measured under both compressed conditions (3.7 psia) and uncompressed conditions in simulated noon and earth-umbra orbit-positions. The range of conductance increased from 0.26 Btu/sq ft-hr degrees F uncompressed to 0.81 Btu/sq ft-hr degree F compressed. Measurements were made in simulated noon and earth-umbra orbit positions of the thermal heat dissipating capability of a louver system which was designed for operation in the sun. A 6-inch square model had a net heat flow from the louvers for the four orbit conditions tested (open and closed in the sun and in the shade). The louver operation controls maintained the louver baseplate temperature in the range from 73.9 to 84.7 F for a steady heat dissipation rate of 95.5 Btu/sq ft-hr while operating in the shade.
Report Availability
Full text available
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AMRLTR67-128.pdf