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Author Sugimura, R. S. ♦ Russo, S. C. ♦ Gilman, D. C.
Source United States Department of Energy Office of Scientific and Technical Information
Content type Text
Language English
Subject Keyword ENGINEERING NOT INCLUDED IN OTHER CATEGORIES ♦ HEAT PIPES ♦ SPACE FLIGHT ♦ NASA ♦ EXPERIMENT PLANNING ♦ CRYOGENICS ♦ SPACE SHUTTLES ♦ COOLING SYSTEMS ♦ HEATING SYSTEMS ♦ LAUNCHING ♦ MECHANICAL VIBRATIONS ♦ TEMPERATURE CONTROL
Abstract The Cryo System Experiment was developed to validate in near zero-g space a 65 K cryogenic system for focal planes, optics, or other imaging instruments that require continuous cryogenic cooling. Two key cryogenic technologies, designed to improve performance of systems for scientific, commercial and defense applications in space, were successfully demonstrated on NASA{close_quote}s recent shuttle mission, Discovery (STS 63), launched on February 3{endash}11, 1995. The two advanced cryogenic technologies consisted of a 2-watt 65 K long-life low-vibration Stirling cooler, and a diode oxygen heat pipe thermal switch. Presented are highlights of the flight experiment and the effectiveness of lessons learned from the system integration of cryocooler and heat pipe technologies relating to: launch-vibration constraints for the expander cold-tips, a high-compliance thermal strap to minimize side loads on the expander, and the value of on-orbit diagnostics to check status of the cryocooler. {copyright} {ital 1996 American Institute of Physics.}
ISSN 0094243X
Educational Use Research
Learning Resource Type Article
Publisher Date 1996-03-01
Publisher Place United States
Volume Number 361
Issue Number 1
Technical Publication No. CONF-960109-


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