JWST NIRSpec mechanical design

Salvignol, Jean-Christophe; Honnen, Karl; Barho, Reiner

doi:10.1117/12.789858

Cited by 5 publications

(2 citation statements)

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“…NIRSpec features an almost all reflective design with an optical bench manufactured out of Silicon-Carbide. 3 It offers four different observing modes: 1) integral field spectroscopy (IFS) 4 via an image slicer, 5 2) multi-object spectroscopy (MOS) 6 via a micro-shutter array that employs about 250,000 individually addressable shutters, 7 3) fixed slit (FS) spectroscopy via several long slits, and 4) bright object times series (BOTS) 8 observations via a dedicated square aperture. In all observing modes the same selection of seven dispersers is available: one prism and six gratings selected via a grating wheel assembly, 9 offering a wavelength coverage from ∼0.6 to 5.3 µm with varying spectral resolution.…”

Section: Introductionmentioning

confidence: 99%

The in-flight noise performance of the JWST/NIRSpec detector system

Birkmann¹,

Giardino

Sirianni³

et al. 2022

Space Telescopes and Instrumentation 2022: Optical, Infrared, and Millimeter Wave

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The Near-Infrared Spectrograph (NIRSpec) is one the four focal plane instruments on the James Webb Space Telescope (JWST) which was launched on December 25, 2021. We present the in-flight status and performance of NIRSpec's detector system as derived from the instrument commissioning data as available at the time of the conference. The instrument features two 2048 × 2048 HAWAII-2RG sensor chip assemblies (SCAs) that are operated at a temperature of about 42.8 K and are read out via a pair of SIDECAR ASICs. NIRSpec supports "Improved Reference Sampling and Subtraction" (IRS2) readout mode that was designed to meet NIRSpec's stringent noise requirements and to reduce 1/f and correlated noise. In addition, NIRSpec features subarrays optimized for bright object time series observations, e.g. for the observation of exoplanet transit around bright host stars. We focus on the dark signal as well as the read and total noise performance of the detectors.

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Section: Introductionmentioning

confidence: 99%

The in-flight noise performance of the JWST/NIRSpec detector system

Birkmann¹,

Giardino

Sirianni³

et al. 2022

Space Telescopes and Instrumentation 2022: Optical, Infrared, and Millimeter Wave

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“…Therefore it is main ly used to support optics and sensitive equipment. For examp le, the kinematic mounting is used for the James Webb Space telescope to connect all the scientific instruments, which contain FGS, NIRSpec, NIRCam, and MIRI, to the ISIM structure [1][2][3] .The scientific instruments on Hubble Space Telescope are connected to the main body structure via the kinemat ic mount [4] .The main optical elements of the Spitzer telescope are connected to the back-end instrument platform through the kinematic mount [5] .…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of the kinematic mount between the space camera and the satellite platform

Sun

Xue

et al. 2023

Advanced Fiber Laser Conference (AFL2022)

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A kinematic mount based on the statically determinate principle is designed using a single-axis right circular flexure hinge. The main role of this support structure is to reduce the influence the satellite platform on the space camera, thereby ensuring the thermal stability of the space camera in orbit. The mathematical model of the compliance of the single-axis right circular flexure hinge is derived based on the Castigliano’s second theorem. According to the index requirements and the compliance equations, the initial structure of kinematic mount is obtained. The optimization design is conducted with the initial structure as the optimization object and the natural frequency as the optimization objective to obtain the optimal structure. The finite element analysis shows that the optimal structure meets the index requirements. Compared with the initial structure, the natural frequency of the optimal structure is increased by 4.2%, the optimal structure in Rx, Ty, and Tz are better than the initial structure 13.3%, 21%, and 12.8%. Experiment verifications of compliance equation C33 of single-axis right circular flexure hinge and the compliance of the bipod are carried out. The experiment results indicate that the compliance equation C33 is correct, and the compliance of the bipod meets the design value. Therefore, it is concluded that all the compliance equations are correct, and the kinematic mount can meet the requirements of the thermal stability of the space camera in orbit.

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Design, analysis, and testing of kinematic mount for astronomical observation instrument used in space camera

Zhang

et al. 2016

Review of Scientific Instruments

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A statically determinate kinematic mount structure is designed for an astronomical observation instrument. The basic principle of the proposed kinematic mount is introduced in detail, including the design principle, its structure, and its degrees of freedom. The compliance equations for the single-axis right circle flexure hinge are deduced, and mathematical models of the compliances of the bipod in the X-axis and Z-axis directions are established. Based on the index requirements, the range of one design parameter (the hinge groove depth, R) for the kinematic mount is determined. Parametric design is performed, with the entire structure being the design object and the first three eigenfrequencies as the design objective; the final design parameter for the kinematic mount is 1.9 mm. The first three eigenfrequencies of the final structure are 36.49 Hz, 38.65 Hz, and 72.41 Hz, which meet the frequency requirements. The Z-direction deformation and the bipod compliances in the X-axis and Z-axis directions are analyzed through simulations and experiments. The results show that (1) the Z-direction deformation of the bipod meets the displacement requirement; (2) the deviations between the finite element results and the compliance equation C results, and between the finite element results and the compliance equation C results are 8.8% and 3.92%, respectively; (3) the deviation between the experimental results and the compliance equation C results is 10.3%. It is concluded that the bipod compliance equations in the X-axis and Z-axis directions are valid, and that the kinematic mount thus meets the design requirements.

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JWST NIRSpec mechanical design

Cited by 5 publications

References 0 publications

The in-flight noise performance of the JWST/NIRSpec detector system

The in-flight noise performance of the JWST/NIRSpec detector system

Design and analysis of the kinematic mount between the space camera and the satellite platform

Design, analysis, and testing of kinematic mount for astronomical observation instrument used in space camera

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