Thermal design of Infrared Space Observatory (ISO) payload dual cooling

Details Thermal design of Infrared Space Observatory (ISO) payload dual cooling Thermal design of Infrared Space Observatory (ISO) payload dual cooling

Dec 1983

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1983esasp.200..179f&link_type=abstract

In ESA Environ. and Thermal Control Systems for Space Vehicles p 179-190 (SEE N84-19396 10-18)

Physics

Optics

Cooling Systems, Cryogenic Cooling, Infrared Astronomy, Infrared Telescopes, Satellite Design, Spaceborne Astronomy, Cassegrain Optics, Cryogenic Equipment, Cryostats, European Space Programs, Liquid Helium 2, Liquid Hydrogen, Systems Simulation

Scientific paper

The thermal design and performance of a spaceborne IR telescope are outlined. The dual cooling system uses superfluid helium (1.5 K) to provide the required temperatures for semiconductor devices, mirrors, and telescope baffle. Liquid hydrogen (20 K) absorbs external heat and provides a suitable environment for the helium system. Two 750l tanks contain the coolants. The fluid management system, thermal layout, and thermal analysis are described. Computer simulations indicate that the detector and optics designs are compatible with an operational lifetime 18 months.

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