Camera and spectrometer on the James Webb Space Telescope
MIRIMIRI being integrated into ISIM, 2013MIRI's cooling system being testedMIRI is uncrated at Goddard Space Flight Center, 2012Infographic of James Webb Space Telescope instruments and their observation ranges of light by wavelength
MIRI uses silicon arrays doped with arsenic to make observations at these wavelengths.[1] The imager is designed for wide views but the spectrograph has a smaller view.[1] Because it views the longer wavelengths it needs to be cooler than the other instruments (see Infrared astronomy), and it has an additional cooling system.[1] The cooling system for MIRI includes a pulse tube precooler and a Joule-Thomson loop heat exchanger.[1] This allowed MIRI to be cooled down to a temperature of 7 kelvins during operations in space.[1]
MIRI was built by the MIRI Consortium, a group that consists of scientists and engineers from 10 different European countries (The United Kingdom, France, Belgium, the Netherlands, Germany, Spain, Switzerland, Sweden, Denmark, and Ireland) with the United Kingdom heading the European consortium,[3] as well as a team from the Jet Propulsion Lab in California, and scientists from several U.S. institutions.[4]
Overview
The spectrograph can observe wavelengths between 4.6 and 28.6 microns, and it has four separate channels, each with its own gratings and image slicers.[2] The field of view of the spectrograph is 3.5 by 3.5 arcseconds.[2]
The spectrograph is capable of low-resolution spectroscopy (LRS) with or without a slit, as well as medium-resolution spectroscopy (MRS) taken with an integral field unit (IFU). This means that MRS with the IFU creates an image cube. Similar to other IFUs this can be compared to an image that has a spectrum for each pixel.[5]
The imager has a plate scale of 0.11 arcseconds/pixel and a field of view of 74 by 113 arcseconds.[6] Earlier in development the field of view was going to be 79 by 102 arcseconds (1.3 by 1.7 arcmin).[2] The imaging channel has ten filters available and the detectors are made of arsenic-doped silicon (Si:As).[1] The detectors (one for the imager, and two for the spectrometer) each have a resolution of 1024x1024 pixels, and they are called Focal Plane Modules or FPMs.[7]
During 2013 and finishing in January 2014, MIRI was integrated into the Integrated Science Instrument Module (ISIM).[8] MIRI successfully passed Cryo Vac 1 and Cryo Vac 2 tests as part of ISIM in the 2010s.[8] MIRI was developed by an international consortium.[8]
MIRI is attached to the ISIM by a carbon-fiber and plastic hexapod structure, which attaches it to the spacecraft but also helps thermally isolate it.[1] (see also Carbon fiber reinforced plastic)
Most of MIRI is located in the main ISIM structure, however the cryocooler is in region 3 of ISIM which is located in the spacecraft bus.[10]
The imager module of MIRI also includes the Low Resolution Spectrometer that can perform long-slit and slitless spectroscopy from 5 to 12 μm light wavelength.[11] The LRS uses Ge (germanium) and ZnS (zinc sulfide) prisms to cause spectroscopic dispersion.[11]
Commissioning is complete as of the following dates:
Imaging, 06/17/2022
Low resolution spectroscopy, 06/24/2022
Medium resolution spectroscopy, 06/24/2022
Coronagraphic imaging, 06/29/2022
Cryocooler
To allow mid-infrared observations within the JWST, the MIRI instrument has an additional cooling system. It works roughly similar to how most refrigerators or an air-conditioner works: a fluid is brought down to a cold temperature in the warm section, and sent back to the cold section where it absorbs heat, then it goes back to the condenser. One source of heat is the left-over heat of the spacecraft, but another is the spacecraft's own electronics, some of which are close to the actual instruments to process data from observations. Most of the electronics are in the much warmer spacecraft bus, but some of the electronics needed to be much closer, and great lengths were taken to reduce the heat they produce. By reducing how much heat the electronics make on the cold side, less heat needs to be removed.
In this case the JWST cryocooler resides in the spacecraft bus and it has lines of coolant that run to the MIRI instrument, chilling it. The cryocooler has a heat radiator on the spacecraft bus to emit the heat it collects.[12] In this case the cooling system uses helium gas as the refrigerant.
The James Webb Space Telescope's cryocooler is based originally on the TRW ACTDP cryocooler.[12] However, the JWST has had to develop a version to handle higher thermal loads.[13] It has a multi-stage pulse tube refrigerator that chills an even more powerful cooler.[12] That is a linear-motion Oxford-style compressor that powers a J-T loop.[13] Its target is to cool the MIRI instrument down to 6 kelvins (−448.87 °F, or −267.15 °C).[12] The ISIM is at about 40 K (due to the sunshield) and there is a dedicated MIRI radiation shield beyond which the temperature is 20 K.[12] The J-T loop is a Joule–Thomson loop heat exchanger.[1]
Filters
MIRI imaging filters
MIRI imaging has 10 filters available for observations.[14]
F560W - Broadband Imaging
F770W - PAH, broadband imaging
F1000W - Silicate, broadband imaging
F1130W - PAH, broadband imaging
F1280W - Broadband imaging
F1500W - Broadband imaging
F1800W - Silicate, broadband imaging
F2100W - Broadband imaging
F2550W - Broadband imaging
F2550WR - Redundant filter, risk reduction
FND - For bright target acquisition
Opaque - Darks
MIRI Coronagraphic imaging has 4 filters available for observations.[14]
F1065C - useful for ammonia and silicates
F1140C
F1550C
F2300C
The low-resolution spectrometer (LRS) uses a double zinc sulfide/germanium (ZnS/Ge) prism. The slit mask has a filter that blocks light with a wavelength shorter than 4.5 μm. LRS covers 5 to 14 μm.[14]
The medium-resolution spectrometer (MRS) has 4 channels that are observed simultaneously. Each channel is however further divided into 3 different spectral settings (called short, medium and long). In one observation MIRI can only observe one of those three settings. An observation that aims to observe the entire spectrum has to carry out 3 separate observations of the individual settings. MRS covers 4.9 to 27.9 μm.[14]
Diagrams
Diagram of MIRI and its cooler, showing the connections between the different systems related to their location. Region 3 is inside the spacecraft bus of JWST
Color-coded and labeled diagram of the MIRI instrument without cryocooler
Diagram highlighting ISIM, which shows the location of the MIRI cryocooler (color-code blue in ISIM Region 3) in the spacecraft bus, on the other side of the heat shield from the instrument.
See also
Spitzer Space Telescope (NASA's mid-infrared space telescope launched in 2003, it could not see as deep into the infrared when its coolant supply was depleted in 2009)
^Bouchet, Patrice; García-Marín, Macarena; Lagage, P.-O.; Amiaux, Jérome; Auguéres, J.-L.; Bauwens, Eva; Blommaert, J. A. D. L.; Chen, C. H.; Detre, Ö. H.; Dicken, Dan; Dubreuil, D.; Galdemard, Ph.; Gastaud, R.; Glasse, A.; Gordon, K. D.; Gougnaud, F.; Guillard, Phillippe; Justtanont, K.; Krause, Oliver; Leboeuf, Didier; Longval, Yuying; Martin, Laurant; Mazy, Emmanuel; Moreau, Vincent; Olofsson, Göran; Ray, T. P.; Rees, J.-M.; Renotte, Etienne; Ressler, M. E.; et al. (2015). "The Mid-Infrared Instrument for the James Webb Space Telescope, III: MIRIM, the MIRI Imager". Publications of the Astronomical Society of the Pacific. 127 (953): 612–622. arXiv:1508.02488. Bibcode:2015PASP..127..612B. doi:10.1086/682254. S2CID119287719.
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