The use of high thermal conductivity composites in the satellite bus structure of the wide field infrared explorer

Details The use of high thermal conductivity composites in the satellite bus structure of the wide field infrared explorer The use of high thermal conductivity composites in the satellite bus structure of the wide field infrared explorer

Jan 1997

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1997aipc..387..573p&link_type=abstract

Space technology and applications international forum (STAIF - 97). AIP Conference Proceedings, Volume 387, pp. 573-580 (1997).

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Nonelectronic Thermal Conduction And Heat-Pulse Propagation In Solids, Thermal Waves, Fullerenes And Related Materials, Artificial Earth Satellites, Space-Based Ultraviolet, Optical, And Infrared Telescopes

Scientific paper

The Wide-field Infrared Explorer (WIRE) spacecraft, the fifth of NASA's Small Explorer (SMEX) series of scientific satellites, is scheduled to be launched in mid 1998 by a Pegasus XL launch vehicle. The WIRE mission will conduct a wide field infrared survey in search for galaxies with an unusually high star formation rate. Once detected, these interesting galaxies can be studied more closely with ground based observatories or with on-orbit telescopes. To maximize the mass allocated to the spacecraft's single infrared telescope, the spacecraft will utilize a lightweight, fully bonded fiber reinforced composite structure. The use of composite materials presents unique challenges to the design of the spacecraft's relatively simple passive thermal control system and necessitates the use of Amoco's high thermal conductivity K1100X fibers in specific areas of the structure. This paper describes the spacecraft's passive thermal control system and focuses on the engineering design, analyses and tests performed to insure the proper mechanical and thermal implementation of high conductivity composites into the WIRE structure.

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