Proceedings Paper
The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope| Format | Member Price | Non-Member Price |
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Paper Abstract
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.
Paper Details
Date Published: 29 September 2004
PDF: 8 pages
Proc. SPIE 5495, Astronomical Structures and Mechanisms Technology, (29 September 2004); doi: 10.1117/12.550023
Published in SPIE Proceedings Vol. 5495:
Astronomical Structures and Mechanisms Technology
Joseph Antebi; Dietrich Lemke, Editor(s)
PDF: 8 pages
Proc. SPIE 5495, Astronomical Structures and Mechanisms Technology, (29 September 2004); doi: 10.1117/12.550023
Show Author Affiliations
Niels Christian Jessen, Danish Space Research Institute (Denmark)
Hans Ulrik Norgaard-Nielsen, Danish Space Research Institute (Denmark)
Tim Stevenson, Univ. of Leicester (United Kingdom)
Hans Ulrik Norgaard-Nielsen, Danish Space Research Institute (Denmark)
Tim Stevenson, Univ. of Leicester (United Kingdom)
Jonathan Sykes, Univ. of Leicester (United Kingdom)
Jorgen Schroll, XPERION (Denmark)
Peter Hastings, UK Astronomy Technology Ctr. (United Kingdom)
Jorgen Schroll, XPERION (Denmark)
Peter Hastings, UK Astronomy Technology Ctr. (United Kingdom)
Published in SPIE Proceedings Vol. 5495:
Astronomical Structures and Mechanisms Technology
Joseph Antebi; Dietrich Lemke, Editor(s)
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