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

Niels Christian Jessen; Hans Ulrik Nørgaard-Nielsen; J Schroll; J Sykes; T Stevenson; P Hastings

doi:10.1117/12.550023

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

Niels Christian Jessen, Hans Ulrik Nørgaard-Nielsen, J Schroll, J Sykes, T Stevenson, P Hastings

Research output: Chapter in Book/Report/Conference proceeding › Article in proceedings › Research › peer-review

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.

Original language	English
Title of host publication	Astronomical Structures and Mechanisms Technology
Volume	5495
Publisher	SPIE - International Society for Optical Engineering
Publication date	2004
ISBN (Print)	978-0819454270
DOIs	https://doi.org/10.1117/12.550023
Publication status	Published - 2004
Event	SPIE Astronomical Telescopes + Instrumentation 2004 - Glasgow, United Kingdom Duration: 21 Jun 2004 → 25 Jun 2004

Conference

Conference	SPIE Astronomical Telescopes + Instrumentation 2004
Country/Territory	United Kingdom
City	Glasgow
Period	21/06/2004 → 25/06/2004

Access to Document

10.1117/12.550023

OpenUrl availability

Full text

Cite this

@inproceedings{2e757f6a6eee48d1b51175002cbd9bdb,

title = "The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope",

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.",

author = "Jessen, {Niels Christian} and N{\o}rgaard-Nielsen, {Hans Ulrik} and J Schroll and J Sykes and T Stevenson and P Hastings",

year = "2004",

doi = "10.1117/12.550023",

language = "English",

isbn = "978-0819454270",

volume = "5495",

booktitle = "Astronomical Structures and Mechanisms Technology",

publisher = "SPIE - International Society for Optical Engineering",

note = "SPIE Astronomical Telescopes + Instrumentation 2004 ; Conference date: 21-06-2004 Through 25-06-2004",

}

Jessen, NC, Nørgaard-Nielsen, HU, Schroll, J, Sykes, J, Stevenson, T & Hastings, P 2004, The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope. in Astronomical Structures and Mechanisms Technology. vol. 5495, SPIE - International Society for Optical Engineering, SPIE Astronomical Telescopes + Instrumentation 2004, Glasgow, United Kingdom, 21/06/2004. https://doi.org/10.1117/12.550023

The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope. / Jessen, Niels Christian; Nørgaard-Nielsen, Hans Ulrik; Schroll, J et al.
Astronomical Structures and Mechanisms Technology. Vol. 5495 SPIE - International Society for Optical Engineering, 2004.

Research output: Chapter in Book/Report/Conference proceeding › Article in proceedings › Research › peer-review

TY - GEN

T1 - The CFRP primary structure of the MIRI instrument onboard the James Webb Space Telescope

AU - Jessen, Niels Christian

AU - Nørgaard-Nielsen, Hans Ulrik

AU - Schroll, J

AU - Sykes, J

AU - Stevenson, T

AU - Hastings, P

PY - 2004

Y1 - 2004

N2 - 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.

AB - 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.

U2 - 10.1117/12.550023

DO - 10.1117/12.550023

M3 - Article in proceedings

SN - 978-0819454270

VL - 5495

BT - Astronomical Structures and Mechanisms Technology

PB - SPIE - International Society for Optical Engineering

T2 - SPIE Astronomical Telescopes + Instrumentation 2004

Y2 - 21 June 2004 through 25 June 2004

ER -

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

Abstract

Conference

Access to Document

OpenUrl availability

Fingerprint

Cite this