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.
Astronomical Structures and Mechanisms Technology, 2004
Main Research Area:
SPIE -The International Society for Optical Engineering, 2004
SPIE - International Society for Optical Engineering