The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope

Details The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope

Sep 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004spie.5495...23j&link_type=abstract

Astronomical Structures and Mechanisms Technology. Edited by Antebi, Joseph; Lemke, Dietrich. Proceedings of the SPIE, Volume 54

Astronomy and Astrophysics

Astronomy

Scientific paper

The design of the Primary Structure of the Mid Infra-Red Instrument (MIRI) onboard the NASA/ESA James Webb Space Telescope will be presented. The main design driver is the energy flow from the 35 K "hot" satellite interface to the 7 K "cold" MIRI interface. Carbon fibre reinforced plastic (CFRP) was chosen for this application due to the low thermal conductivity at cryogenic temperatures, high strength and low density. Details of the qualification program will be given.

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