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

Jessen, Niels Christian; Nørgaard-Nielsen, H. U.; Stevenson, Tim; Sykes, J.; Schroll, Jorgen; Hastings, Peter

doi:10.1117/12.550023

Cited by 10 publications

(10 citation statements)

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“…The completed OM is mounted to the JWST ISIM via a carbon fibre reinforced polymer (CFRP) hexapod mounting system (the black rods in Figure 1). This hexapod thermally isolates the OM from ISIM, which is passively cooled to about 40 K, while supporting it against the mechanical loads encountered during launch (Jessen et al 2004).…”

Section: Optical Bench Assemblymentioning

confidence: 99%

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The Mid-Infrared Instrument for JWST, II: Design and Build

Wright,

Goodson

et al. 2015

Preprint

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The Mid-InfraRed Instrument (MIRI) on the James Webb Space Telescope (JWST) provides measurements over the wavelength range 5 to 28.5 µm. MIRI has, within a single 'package', four key scientific functions: photometric imaging, coronagraphy, single-source low-spectral resolving power (R ∼ 100) spectroscopy, and medium-resolving power (R ∼ 1500 to 3500) integral field spectroscopy. An associated cooler system maintains MIRI at its operating temperature of <6.7 K. This paper describes the driving principles behind the design of MIRI, the primary design parameters, and their realisation in terms of the 'as-built' instrument. It also describes the test programme that led to delivery of the tested and calibrated Flight Model to NASA in 2012, and the confirmation after delivery of the key interface requirements.

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Section: Optical Bench Assemblymentioning

confidence: 99%

“…The chosen design solution for the hexapod is six struts of length 405mm, diameter 35.5mm and 1.2mm wall thickness. This sizing avoids buckling under the design load and maintains a damage-tolerant wall thickness (Jessen et al 2004).…”

Section: Hexapod Design and Testmentioning

confidence: 99%

The Mid-Infrared Instrument for JWST, II: Design and Build

Wright,

Goodson

et al. 2015

Preprint

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“…Largely thermal considerations have led the JWST MIRI European Consortium to specify a carbon fibre–reinforced polymer (CFRP) hexapod with rigidised invar end fittings and brackets to form part of the ‘primary structure’ of the instrument. 4 Each bracket incorporates a pair of orthogonal flexures to provide quasi-kinematic mounting to JWST.…”

Section: Introductionmentioning

confidence: 99%

“…The instrument optical bench assembly is of isothermal construction in aluminium alloy in order to maintain internal alignment as the instrument cools from ambient to 6 K. The instrument is contained within the Integrated Science Instrument Module (ISIM) of the spacecraft, which is kept at ;40 K. To minimise loads on the MIRI cryocooler, the MIRI primary structure must provide thermal isolation. This is achieved by a carbon fibre hexapod, 4 supplied by Technical University of Denmark, with invar end fittings and brackets that connect to an aluminium optical bench, called the deck (Figure 1(b)), supplied by the University of Leicester. At each apex of each hexapod bipod, the CFRP struts connect to invar brackets via invar end fittings.…”

Section: Miri and Primary Structure Descriptionmentioning

confidence: 99%

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Space-compatible strain gauges as an integration aid for the James Webb Space Telescope Mid-Infrared Instrument

Samara-Ratna

Sykes

Bicknell

et al. 2014

The Journal of Strain Analysis for Engineering Design

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Space instruments are designed to be highly optimised, mass efficient hardware required to operate in extreme environments. Building and testing is extremely costly, and damage that appears to have no impact on performance at normal ambient conditions can have disastrous implications when in operation. The Mid-Infrared Instrument is one of four instruments to be used on the James Webb Space Telescope which is due for launch in 2018. This telescope will be successor to the Hubble Space Telescope and is the largest space-based astronomy project ever to be conceived. Critical to operation of the Mid-Infrared Instrument is its primary structure, which provides both a stable platform and thermal isolation for the scientific instruments. The primary structure contains strain-absorbing flexures and this article summarises how these have been instrumented with a novel strain gauge system designed to protect the structure from damage. Compatible with space flight requirements, the gauges have been used in both ambient and cryogenic environments and were successfully used to support various tasks including integration to the spacecraft. The article also discusses limitations to using the strain gauge instrumentation and other implications that should be considered if such a system is to be used for similar applications in future.

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