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Shuttle Launch Entry Suit Liquid Cooling System Thermal Performance
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English
Abstract
A thermoelectric liquid cooling system recently developed at the Johnson Space Center was evaluated in manned and unmanned ground tests as an alternative to the Space Shuttle launch and entry suit personal fan. The liquid cooling system provided superior cooling in environments simulating flight deck conditions during launch and postlanding.
Authors
Citation
Bue, G., Conger, B., Hooper, P., Chang, C. et al., "Shuttle Launch Entry Suit Liquid Cooling System Thermal Performance," SAE Technical Paper 951546, 1995, https://doi.org/10.4271/951546.Also In
References
- Chang, C. Bue, G. “Liquid Cooled Launch and Entry Suit Test Program Document,” JSC document JSC-37738 February 1993
- Waligora, J. Kumar, K. “Use of Liquid Cooling in the Launch and Entry Suit - Phase II,” NASA document SD5-94-JMW1 February 1994
- Waligora, J. “Thermal Comfort and Tolerance Design Criteria,” NASA document BRO DB-57-67 B September 1967
- Savage, M. Brengelmann, G. “Control of skin blood flow in humans in the neutral zone,” Journal of Applied Physiology
- Chang, C. Bue, G. “Space Shuttle Launch Entry Suit Thermal Performance Evaluation,” Technical Paper, 23rd ICES July 1993