DOCSLIB.ORG

Power Distribution for Cryogenic Instruments at 6-40K the James Webb Space Telescope Case

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Power Distribution for Cryogenic Instruments at 6-40K the James Webb Space Telescope Case Power Distribution for Cryogenic Instruments at 6-40K The James Webb Space Telescope Case Peter Rumler<1>, Ray Lundqu ist<2>, Jose Lorenzo Alvarez'll , Jeff Since 11<2>, Jim Tutt1e<2> fl ) ESA-ESTEC, 2200AG Noordwijk. Nether/ands, JNh'r.ru111/cr'!! l!sa.1111 <1JNASA-GSFC, Greenbelt, MD-20771 USA, my.a./1111d,111isr'if,11a.1·a .1?01· \ .. -- ABSTRA CT ISIM structure located in Region I of the JWST Observatory. Each instrument's OA is connected The Integrated Science Instrument Module (ISIM) of through a heat strap to a dedicated radiator that the James Webb Space Telescope (JWST) operates its provides passive cooling to temperatures below 40K. instruments passively cooled at around 40 Kelvin (K), In addition, the NIRSpec FPA and the SIDECAR ASIC with a warm Instrument Electronic Compartment (!EC) (System for Image Digitization, Enhancement. Control at 300K attached to it. From the wann electronics all and Retrieval) connect to a dedicated radiator separate secondary signal and power harnesses have to bridge from the NIRSpec OA radiator. The ISIM Structure is this 300-40K temperature difference and minimize the a frame made of square graphite fiber reinforced plastic power dissipation and parasitic heat leak into the cold (GFRP) tubes attached together with gussets and clips, region. and with metal fittings for the Optical Telescope After an introduction of the !SIM with its instruments, Element (OTE) and Science Instrument interfaces. The the IEC with the electronics, and the harness resistivity of the GFRP tube material has been architecture with a special radiator, this paper measured to be in the order of H'l/m, and the resistance \ elaborates on the cryogenic wire selection and tests of the joints between GFRP tubes has been measured to perfonned to establish current de-rating rules for be approximately 10-200! per joint. The resulting different wire types. Finally failure modes are analyzed overall IS IM structure resistance of IO- I oon from the for critical instrument interfaces that could inject OAs to the IEC ground cannot be considered as a low excessive currents and heat into the harness and cold impedance ground plane in Region I. side, and several solutions for the removal of such failures are presented. 1. INTRODUCTION The James Webb Space Telescope (JWST) is an Infrared Space Observatory that will follow-up Hubble in 2016, designed by NASA with contributions from Region 1 ESA and the Canadian Space Agency (CSA). ESA ISIM Structure, provides the Ariane-5 Launch vehicle for JWST and Optic.ii Auemblln supplies the Near Infrared Spectrograph (NIRSpec) and 35-40!( the science part of the Mid Infrared Instrument (M IRI). CSA provides an instrument with a Fine Guidance Sensor (FGS) and tuneable Filter. JWST features a sunshield approximately the size of a tennis court that passively cools the Integrated Science Instrument Region 2 .Module (ISIM) with the infrared instruments. IEC Figure I shows JWST in stowed (launch) configuration 2T3-313K without the sunshield and the three thennal regions Region 3 where instrument components are located. Spacecraft ICOH 2. ISIM OVERVIEW The !SIM is the Payload Element of the JWST, Figure 1. /SIM Component Regions on the JWST containing the Near-Infrared Camera· (NIRCam), Observatory NIRSpec, MIRI, and FGS. The optical assemblies (OA) of the instruments contain the optics, the 2.1 Instruments Electronics Compartment (IEC) respective Focal Plane Assemblies (FPA) with infrared The control electronics for each instrument are detectors and mechanisms, and they are mounted to the contained in the IEC, where the temperature will be • maintained between 273K and 3 13K. The large temperature gradient between Region I and Region 2 NIRSpec requires the use of thermally resistive materials to NIRSpec is a large field of view spectrograph that prevent heat transfer. contains 2 SCAs passively cooled to 38K, each of As a result, all harnesses between Regions I and 2 are which is controlled by a SIDECAR ASIC. The cryogenic harnesses that will have relatively high wire NIRSpec FPE controls the SIDECAR ASICS, and it and shield electrical resistance. Still, they provide a interfaces to the IRSU over SpaceWire. The NIRSpec better ground connection between Regions I and 2 than ICE box controls the mechanisms in Region I with the the structure. The ground impedance is in the order of exception of the Microshutter Array (MSA), which is 1-1011 when using all shield wires (mostly stainless managed by the NIRSpec Microshutter Control steel shields) in parallel for one instrument. Figure 2 Electronics (MCE) box. shows the layout of ISIM and IEC with the interconnecting harnesses. FGS Guider and Tuneable Filter In addition to the instrument control electronics, the The FGS-Guider is used to facilitate fine pointing of IEC contains the JSIM Remote Services Unit (IRSU), the Observatory by providing the Spacecraft with the which provides SpaceWire interfaces to the instrument precise location of a guide star's image in its field of Focal Plane Electronics (FPE) for science data view at 16Hz. FGS includes three separate chains: transmission, as well as thermal control for ISIM Guider-I, Guider-2 and the Tuneable Filter (TF). Each Region I. The command and data handling functions chain consists of one SCA with associated SIDECAR for the instruments are provided by the ISIM ASIC, and a dedicated FPE/ICE module in the FGS Command and Data Handling (ICDH) unit in Region 3 electronics box in the IEC. via a MIL-1553 bus. And the Power Control Unit (PCU) in the spacecraft supplies all electronic boxes MIRI with a 30V unregulated power bus, with a minimum of MIR! is a combined imager and spectrometer that uses 22V and a maximum of35V. an additional cryo-cooler to actively cool its structure The mass ,estimate for the IEC compartment is 102kg to approximately 7K and its SCAs to 4-6K. The MIRI and 132kg for all electronic boxes inside. SCAs make use of a different technology suitable for the medium infrared range, and they are not compatible with the SIDECAR ASICs. Here the FPE directly controls the SCAs via an analog interface, and provides science data to the IRSU over SpaceWire. The MIRI ICE box controls the MIRI mechanisms in Region I with the exception of the cooler. The cooler is controlled by the ·two Cooler Control Electronics (CCEs for Joule Thomson and Pulse Tube coolers) boxes in Region 3. IRSU & ICDH The IRSU includes a Multi-SpaceWire Concentrator (MSC) with 3 parallel SpaceWire links to the ICDH and the !SIM thermal control electronics. It monitors the Region I cryogenic temperature sensors and lklclr1UI~ provides power to the contamination control heaters on Figure 2. JSJM, /EC and Harness Radiator Layout the instrument OAs. The contamination control heaters maintain the temperatures of critical components above 2.2 Instruments and ISIM Electronics the temperature of the surrounding structure during cool-down. The MSC also distributes a 60MHz clock NIRCam to the FPEs and synchroni zation clocks ( I 00/200/500 NIRCam is a large field of view imager that is kHz) to all instrument electronic boxes. passively cooled to 37K. NIRCam contains 10 Sensor The ICDH contains the ISIM Flight Software and each Chip Assemblies (SCAs), each of which is controlled instrument's Flight Software Application, as well as the by a SIDECAR ASIC, developed by Rockwell SpaceWire interfaces to the IRSU and the ISIM 1553 Scientific for JWST operation at 35-40K. Each of the 2 bus interfaces to the control electronics. On the other NIRCam FPE modules in Region 2 controls the side the ICDH interfaces to the Solid State Recorder interface to 5 SIDECAR ASICS in Region I, and it (SSR) over SpaceWire and to the Spacecraft Command interfaces to the IRSU over SpaceWire. The NIRCam and Telemetry Processor (CTP) over the S/C-ISIM Instrument Control Electronics (ICE) box controls the I 553 Bus (see Fig. 3 ). mechanisms in Region I. I ,. REGION2 COiOt. .... , ..... REGION l Figure 3. /SIM Electrical Connection Diagram 3. HARNESS ARCHITECTURE Region 2 harnesses comprise all harnesses inside the IEC. On the Spacecraft side they connect the The Region I harnesses include all the harnesses on the electronics boxes to the Region 3 interface (power, instrument OAs and the !SIM Structure, as well as the SpaceWire, 1553-bus and clock/sync) on ICP-3 via the harnesses connecting between the ISIM structure and common !EC cavity, which is called the IEC the IEC via the tray radiator. The boundary to Region 2 Backbone. is at Interface Connector Panels (ICPs) called ICP-2's The power harnesses are made of A WG-20 copper on the IEC. All harnesses from there up to the wires, with at least two parallel wires for electronics interfaces on the instrument OAs (ICP-1 's) are with low power consumption, and up to IO parallel cryogenic harnesses that must accommodate the large wires for the IRSU with a peak power consumption of temperature gradient (300K - 40K). Harnesses inside I6SW. With a one-way length of 15-16m between the the !EC and on the instrument OAs are isothermal and PCU and the electronics in the !EC, this results in a can be made of copper. The exception is MIR! where maximum roundtrip voltage drop of no more than there is a need for cryogenic harnesses from the !SIM 0.75V (nt peak power and 22V at the interface). This mounting interface and ICP-1 at 40K up to the actively leads to a total of 67 A WG-20 pairs of power feeds for cooled OA at 6K. For the ease of integration and the 12 electronic boxes with 21 power interfaces. For testing another series of interface connector panels an average !EC power consumption of 200W (overall (ICP-A 's) has been introduced between the harness peak power is 535W) this seems to be oversized, but radiator and the ISIM enclosure.
Load more

Recommended publications
  • Nircam Optical Analysis
    NIRCam Optical Analysis Yalan Mao, Lynn W. Huff and Zachary A. Granger Lockheed Martin Advanced Technology Center, 3251 Hanover St., Palo Alto, CA 94304 ABSTRACT The Near Infrared Camera (NIRCam) instrument for NASA’s James Webb Space Telescope (JWST) is one of the four science instruments to be installed into the Integrated Science Instrument Module (ISIM) on JWST. NIRCam’s requirements include operation at 37 Kelvin to produce high-resolution images in two wave bands encompassing the range from 0.6 microns to 5 microns. In addition, NIRCam is to be used as a metrology instrument during the JWST observatory commissioning on orbit, during the precise alignment of the observatory’s multiple-segment primary mirror. This paper will present the optical analyses performed in the development of the NIRCam optical system. The Compound Reflectance concept to specify coating on optics for ghost image reduction is introduced in this paper. Key words: NIRCam, JWST, Compound Reflectance, Optical analysis, ghost image 1. INTRODUCTION NIRCam is a science instrument that will make up part of the science instrument complement of the James Webb Space Telescope (JWST). The JWST will possess a large aperture of 6.5m with several times the collecting area of the Hubble Space Telescope. JWST will have a broadband IR capability that, from the vicinity of Lagrange 2 (nine hundred thousand km from earth), will allow a view into the distant history of galaxy formation. The instrument will be required to furnish high-quality infrared imaging performance while operating in a challenging cryogenic (32 - 37 Kelvin) space environment over a minimum 5-year (10 year goal) mission.
    [Show full text]
  • Status of the James Webb Space Telescope Integrated Science Instrument Module System
    The 2010 STScI Calibration Workshop Space Telescope Science Institute, 2010 Susana Deustua and Cristina Oliveira, eds. Status of the James Webb Space Telescope Integrated Science Instrument Module System Matthew A. Greenhouse*, Michael P. Drury, Jamie L. Dunn, Stuart D. Glazer, Ed Greville, Gregory Henegar, Eric L. Johnson, Ray Lundquist, John C. McCloskey, Raymond G. Ohl IV, Robert A. Rashford, and Mark F. Voyton Goddard Space Flight Center, Greenbelt, MD 20771 Abstract. The Integrated Science Instrument Module (ISIM) of the JamesWebbSpace Telescope (JWST) is discussed from a systems perspective with emphasis on devel- opment status and advanced technology aspects. The ISIM is one of three elements that comprise the JWST space vehicle and is the science instrument payload of the JWST. The major subsystems of this flight element and theirbuildstatusare described. 1. Introduction The James Webb Space Telescope (Figure 1) is under development by NASA for launch during 2014 with major contributions from the European and Canadian Space Agencies. The JWST mission is designed to enable a wide range of science investigations across four broad themes: (1) observation of the first luminous objects after the Big Bang, (2) the evolution of galaxies, (3) the birth of stars and planetary systems, and (4) the formation of planets and the origins of life [1],[2],[3]. Integrated Science Instrument Module (ISIM) is the science payload of the JWST [4],[5],[6]. Along with the telescope and spacecraft, the ISIM is one of three elements that comprise the JWST space vehicle. At 1.4 mT, it makes up approximately 20% of both the observatory mass and cost to launch.
    [Show full text]
  • Nircam: Development and Testing of the JWST Near-Infrared Camera
    NIRCam: Development and Testing of the JWST Near-Infrared Camera Thomas Greenea, Charles Beichmanb, Michael Gully-Santiagoc,DanielJaffec, Douglas Kellyd, John Kriste,MarciaRieked, and Eric H. Smithf aNASA’s Ames Research Center, MS 245-6, Moffett Field, CA, USA; bNExScI, Caltech 100-22, Pasadena, CA, USA; cUniversity of Texas Department of Astronomy, Austin, TX, USA; dSteward Observatory, University of Arizona, Tucson, AZ, USA; eJet Propulsion Laboratory, 4800 Oak Grove Drive, Pasadena, CA, USA; fLockheed Martin Advanced Technology Ctr., 3251 Hanover St., Palo Alto, CA USA ABSTRACT The Near Infrared Camera (NIRCam) is one of the four science instruments of the James Webb Space Telescope (JWST). Its high sensitivity, high spatial resolution images over the 0.6 − 5 μm wavelength region will be essential for making significant findings in many science areas as well as for aligning the JWST primary mirror segments and telescope. The NIRCam engineering test unit was recently assembled and has undergone successful cryogenic testing. The NIRCam collimator and camera optics and their mountings are also progressing, with a brass-board system demonstrating relatively low wavefront error across a wide field of view. The flight model’s long-wavelength Si grisms have been fabricated, and its coronagraph masks are now being made. Both the short (0.6 − 2.3 μm) and long (2.4 − 5.0 μm) wavelength flight detectors show good performance and are undergoing final assembly and testing. The flight model subsystems should all be completed later this year through early 2011, and NIRCam will be cryogenically tested in the first half of 2011 before delivery to the JWST integrated science instrument module (ISIM).
    [Show full text]
  • The Mid-Infrared Instrument for JWST I
    When there is a discrepancy between the information in this technical report and information in JDox, assume JDox is correct. The Mid-Infrared Instrument for the James Webb Space Telescope, I: Introduction G. H. Rieke1,G.S.Wright2,T.B¨oker3,J.Bouwman4, L. Colina5, Alistair Glasse2,K.D. Gordon6,7,T.P.Greene8,ManuelG¨udel9,10, Th. Henning4,K.Justtanont11,P.-O. Lagage12,M.E.Meixner6,13, H.-U. Nørgaard-Nielsen14,T.P.Ray15,M.E.Ressler16,E.F. van Dishoeck17,&C.Waelkens18. –2– ABSTRACT MIRI (the Mid-Infrared Instrument for the James Webb Space Telescope (JWST)) operates from 5 to 28.5 μm and combines over this range: 1.) unprece- dented sensitivity levels; 2.) sub-arcsec angular resolution; 3.) freedom from atmospheric interference; 4.) the inherent stability of observing in space; and 1Steward Observatory, 933 N. Cherry Ave, University of Arizona, Tucson, AZ 85721, USA 2UK Astronomy Technology Centre, Royal Observatory, Edinburgh, Blackford Hill, Edinburgh EH9 3HJ, UK 3European Space Agency, c/o STScI, 3700 San Martin Drive, Batimore, MD 21218, USA 4Max-Planck-Institut f¨ur Astronomie, K¨onigstuhl 17, D-69117 Heidelberg, Germany 5Centro de Astrobiolog´ıa (INTA-CSIC), Dpto Astrof´ısica, Carretera de Ajalvir, km 4, 28850 Torrej´on de Ardoz, Madrid, Spain 6Space Telescope Science Institute, 3700 San Martin Drive, Baltimore, MD 21218, USA 7Sterrenkundig Observatorium, Universiteit Gent, Gent, Belgium 8Ames Research Center, M.S. 245-6, Moffett Field, CA 94035, USA 9Dept. of Astrophysics, Univ. of Vienna, T¨urkenschanzstr 17, A-1180 Vienna, Austria 10ETH Zurich, Institute for Astronomy, Wolfgang-Pauli-Str. 27, CH-8093 Zurich, Switzerland 11Chalmers University of Technology, Onsala Space Observatory, S-439 92 Onsala, Sweden 12Laboratoire AIM Paris-Saclay, CEA-IRFU/SAp, CNRS, Universit´e Paris Diderot, F-91191 Gif-sur- Yvette, France 13The Johns Hopkins University, Department of Physics and Astronomy, 366 Bloomberg Center, 3400 N.
    [Show full text]
  • James Webb Space Telescope Is Expected to Have As Profound and Far-Reaching an Impact on Astrophysics As Did Its Famous Predecessor
    JWST Peter Jakobsen & Peter Jensen Directorate of Scientific Programmes, ESTEC, Noordwijk, The Netherlands nspired by the success of the Hubble Space Telescope, NASA, ESA and the Canadian I Space Agency have collaborated since 1996 on the design and construction of a scientifically worthy successor. Due to be launched from Kourou in 2013 on an Ariane-5 rocket, the James Webb Space Telescope is expected to have as profound and far-reaching an impact on astrophysics as did its famous predecessor. Introduction Astronomers cannot conduct experi- ments on the Universe, instead they must patiently observe the night sky as they find it, teasing out its secrets only by collecting and analysing the light received from celestial bodies. Since the time of Galileo, the foremost tool of astronomy has been the telescope, feeding first the human eye, and later increasingly sensitive and sophisticated instruments designed to record and dissect the captured light. With the coming of the Space Age, astronomers soon began sending their telescopes and instrumentation into orbit, to operate above the constraining window of Earth’s atmosphere. One of the most successful astronomical esa bulletin 133 - february 2008 33 Science Who was James Webb? James E. Webb (1906-92) was NASA’s second administrator. Appointed by President John F. Kennedy in 1961, Webb organised the fledgling space agency and oversaw the development of the Apollo programme until his retirement a few months before Apollo 11 successfully landed on the Moon. Although an educator and lawyer by training, with a long career in public service and industry, Webb can rightfully be considered the father of modern space science.
    [Show full text]
  • The Mid-Infrared Instrument for the James Webb Space Telescope, I: Introduction
    The Mid-Infrared Instrument for the James Webb Space Telescope, I: Introduction G. H. Rieke1,G.S.Wright2,T.B¨oker3,J.Bouwman4, L. Colina5, Alistair Glasse2,K.D. Gordon6,7,T.P.Greene8,ManuelG¨udel9,10, Th. Henning4,K.Justtanont11,P.-O. Lagage12,M.E.Meixner6,13, H.-U. Nørgaard-Nielsen14,T.P.Ray15,M.E.Ressler16,E.F. van Dishoeck17,&C.Waelkens18. –2– ABSTRACT MIRI (the Mid-Infrared Instrument for the James Webb Space Telescope (JWST)) operates from 5 to 28.5 μm and combines over this range: 1.) unprece- dented sensitivity levels; 2.) sub-arcsec angular resolution; 3.) freedom from atmospheric interference; 4.) the inherent stability of observing in space; and 1Steward Observatory, 933 N. Cherry Ave, University of Arizona, Tucson, AZ 85721, USA 2UK Astronomy Technology Centre, Royal Observatory, Edinburgh, Blackford Hill, Edinburgh EH9 3HJ, UK 3European Space Agency, c/o STScI, 3700 San Martin Drive, Batimore, MD 21218, USA 4Max-Planck-Institut f¨ur Astronomie, K¨onigstuhl 17, D-69117 Heidelberg, Germany 5Centro de Astrobiolog´ıa (INTA-CSIC), Dpto Astrof´ısica, Carretera de Ajalvir, km 4, 28850 Torrej´on de Ardoz, Madrid, Spain 6Space Telescope Science Institute, 3700 San Martin Drive, Baltimore, MD 21218, USA 7Sterrenkundig Observatorium, Universiteit Gent, Gent, Belgium 8Ames Research Center, M.S. 245-6, Moffett Field, CA 94035, USA 9Dept. of Astrophysics, Univ. of Vienna, T¨urkenschanzstr 17, A-1180 Vienna, Austria 10ETH Zurich, Institute for Astronomy, Wolfgang-Pauli-Str. 27, CH-8093 Zurich, Switzerland 11Chalmers University of Technology, Onsala Space Observatory, S-439 92 Onsala, Sweden 12Laboratoire AIM Paris-Saclay, CEA-IRFU/SAp, CNRS, Universit´e Paris Diderot, F-91191 Gif-sur- Yvette, France 13The Johns Hopkins University, Department of Physics and Astronomy, 366 Bloomberg Center, 3400 N.
    [Show full text]
  • Use of a Pathfinder Optical Telescope Element for James Webb Space Telescope Risk Mitigation
    Use of a Pathfinder Optical Telescope Element for James Webb Space Telescope Risk Mitigation Lee D. Feinberga*, Ritva KeskiKuhaa, Charlie Atkinsonb, Scott C. Texter” aNASA Goddard Space Flight Center, Greenbelt, MD, USA 20771; 1’Northrup Grumman, Redondo Beach, CA USA ABSTRACT A Pathfmder of the James Webb Space Telescope (JWST) Optical Telescope Element is being developed to check out critical ground support equipment and to rehearse integration and testing procedures. This paper provides a summary of the baseline Pathfmder configuration and architecture, objectives of this effort, limitations of Pathfinder, status of its development, and future plans. Special attention is paid to risks that will be mitigated by Pathfmder. Keywords: Space Telescope, JWST, OTE, James Webb Space Telescope, Pathfmder, Risk 1. INTRODUCTION The testing of JWST Optical Telescope Element 1 (OTE) and Integrated Science Instrument System (ISIM) occurs as an integrated entity called the OTE-ISIM (OTIS) at the Johnson Space Center”. In order to assure the test is successful with as few cryogenic cycles as is possible, an OTE Pathfinder is being funded by the prime contractor Northrop Grumman as an IR+D funded effort. NGAS’s current plan emphasizes optical checkout at cryogenic temperatures though an augmentation to the Pathfmder plan is in the process of being added to the program that would add thermal checkout and dynamics objectives. 2. BIsT0RY OF PATHFINDER The OTE Pathfmder has its roots in the Verification Engineering Test Articles implemented on the Chandra program wherein unfinished flight optics were used to aid in the development of, and to demonstrate the integration operations and X-ray optical testing of, the critical optical components of the telescope using GSE that was uniquely designed for the purpose.
    [Show full text]
  • The James Webb Space Telescope Integrated Science Instrument Module Matthew A
    The James Webb Space Telescope Integrated Science Instrument Module Matthew A. Greenhouse*,Pamela C. Sullivan, Leslye A. Boyce, Stuart D. Glazer, Eric L. Johnson, John C. McCloskey, Mark F. Voyton Goddard Space Flight Center, Greenbelt, MD 20771 ABSTRACT The Integrated Science Instrument Module of the James Webb Space Telescope is described fiom a systems perspective with emphasis on unique and advanced technology aspects. The major subsystems of this flight element are described including: structure, thermal, command and data handling, and software. Keywords: JWST, Instrumentation 1. INTRODUCTION The James Webb Space Telescope (JWST) mission (Figure 1) is under development by NASA for launch during 201 1 with major contributions fi-om the European and Canadian Space Agencies. The JWST mission is designed to address four science themes: [ 11 observation of the first luminous objects after the Big Bang, [2] the assembly of these objects into galaxies, [3] the birth of stars and planetary systems, and 141 the formation of planets and the origins of life. The Integrated Science Instrument Module (ISIM) is the science payload of the JWST and is one of three elements that comprise the JWST flight segment (Figure 2). The ISEM contains four science instrument sub-systems, a cryogenic fine guidance sensor, and a wavefi-ont sensor that is used to control the optical figure of the telescope primary mirror. The primary function of the ISM is to provide shared support systems for these instruments and to enable ground verification of the cryogenic payload prior to integration with the telescope. In Figure 2: ISM Element he following sections, we briefly describe the science instruments and their shared support systems including the optical metering structure, passive cryogenic thermal control, command and data handling (ICDH), and ICDH software.
    [Show full text]
  • Nircam Instrument Overview
    NIRCam Instrument Overview Larry G. Burriesci Lockheed Martin Advanced Technology Center 3251 Hanover St., Palo Alto, CA 94304 ABSTRACT The Near Infrared Camera (NIRCam) instrument for NASA’s James Webb Space Telescope (JWST) is one of the four science instruments installed into the Integrated Science Instrument Module (ISIM) on JWST intended to conduct scientific observations over a five year mission lifetime. NIRCam’s requirements include operation at 37 kelvins to produce high resolution images in two wave bands encompassing the range from 0.6 microns to 5 microns. In addition NIRCam is used as a metrology instrument during the JWST observatory commissioning on orbit, during the initial and subsequent precision alignments of the observatory’s multiple-segment 6.3 meter primary mirror. JWST is scheduled for launch and deployment in 2012. This paper is an overview of the NIRCam instrument with pointers to several NIRCam subsystem papers to be presented in the same conference. This paper will introduce and explain at top level the structural, optical, mechanical and thermal subsystems of NIRCam. Keywords: NIRCam, James Webb, JWST, ISIM 1. INTRODUCTION 1.1 Instrument Overview The NIRCam instrument for JWST is one of the four science instruments to be installed into the ISIM. NIRCam’s requirements include operation at 37 kelvins to produce high resolution images in two wave bands encompassing the range from 0.6 microns to 5 microns. In addition NIRCam is to be used as a metrology instrument during the JWST observatory commissioning on orbit during the precise alignment of the observatory’s multiple-segment primary mirror. 1.2 Integrated Science Instrument Module (ISIM) The ISIM occupies the volume directly behind the JWST primary mirror assembly.
    [Show full text]
  • MIRI the Mid-Infrared Instrument for JWST the James Webb Space Telescope
    MIRI The Mid-InfraRed Instrument for JWST The James Webb Space Telescope Prof. Gillian Wright, MBE Science and Technology Facilities Council UK-Astronomy Technology Centre JWST MIRI European PI Talk Overview 6th Appleton Space Conference, RAL, 9 December 2010 James Webb Space Telescope • 6.5m Diameter Primary Mirror • Launch June 2014 (under review) • Infrared Optimised Telescope • Placed in an L2 orbit • Passively cooled to ~ 40K • Mission Lifetime 5-10 years 6th Appleton Space Conference, RAL, 9 December 2010 The JWST Mission • JWST is being built by a collaboration between NASA, ESA and CSA – Europe has a guaranteed 15% share of the observing time • It will be the largest space telescope and mission ever launched • To place such a large telescope in a far away orbit and cool it sufficiently brings unique challenges 6th Appleton Space Conference, RAL, 9 December 2010 Why is JWST an Infrared Telescope ? To help resolve key outstanding questions about the Universe we now need to: 1. Study further into the early universe than is possible with current telescopes and missions – the ultraviolet and visible light from distant sources is red-shifted into the infrared part of the spectrum 2. Look deep into regions where stars and planets are forming – Infrared light is less well absorbed by dust and we can see warm dust directly 6th Appleton Space Conference, RAL, 9 December 2010 JWST Instruments NIRCam • JWST is designed to enable broad FGS science investigations by the world- wide astronomical community – Broad- and narrow-band imagery: 0.6–29
    [Show full text]
  • The James Webb Space Telescope's Plan for Operations And
    The James Webb Space Telescope’s plan for operations and instrument capabilities for observations in the Solar System Stefanie N. Milam1, John A. Stansberry2, George Sonneborn1, Cristina Thomas1,3,4 1NASA Goddard Space Flight Center, 8800 Greenbelt Rd, Greenbelt, MD 20771 ([email protected]; [email protected]; [email protected]) 2Space Telescope Science Institute, 3700 San Martin Drive, Baltimore, MD 21218 ([email protected]) 3NASA Postdoctoral Program Fellow, NASA Goddard Space Flight Center, 8800 Greenbelt Rd, Greenbelt, MD 20771 4Planetary Science Institute, 1700 East Fort Lowell, Suite 106, Tucson, AZ 85719 Abstract: The James Webb Space Telescope (JWST) is optimized for observations in the near and mid infrared and will provide essential observations for targets that cannot be conducted from the ground or other missions during its lifetime. The state-of-the-art science instruments, along with the telescope’s moving target tracking, will enable the infrared study, with unprecedented detail, for nearly every object (Mars and beyond) in the solar system. The goals of this special issue are to stimulate discussion and encourage participation in JWST planning among members of the planetary science community. Key science goals for various targets, observing capabilities for JWST, and highlights for the complementary nature with other missions/observatories are described in this paper. Keywords: Solar System; Astronomical Instrumentation 1. Introduction The James Webb Space Telescope (JWST) is an infrared-optimized observatory with a 6.5m-diameter segmented primary mirror and instrumentation that provides wavelength coverage of 0.6 to 28.5 microns, sensitivity 10X to 100X greater than previous or current facilities, and high angular resolution (0.07 arcsec at 2 microns).
    [Show full text]
  • The New Worlds Probe: a Starshade with JWST NWP Can Do Imaging
    Astro2010 PPP RFI Response The New Worlds Probe: A Starshade with JWST Contacting Author: Webster Cash University of Colorado, Boulder email: [email protected] phone: (303) 492-4056 NWP can do imaging and spectroscopy of terrestrial planets as early as 2016 This may be the fastest and most affordable path to the discovery of life. Co-Authors David Spergel Princeton University Remi Soummer Space Telescope Science Institute Matt Mountain Space Telescope Science Institute Kate Hartman Goddard Space Flight Center Ron Polidan Northrop Grumman Corporation Tiffany Glassman Northrop Grumman Corporation Amy Lo Northrop Grumman Corporation I. SUMMARY The James Webb Space Telescope will be an extraordinary observatory, providing a huge range of exciting new astrophysics results. But it will not be able to directly observe planets in the Habitable Zone of nearby stars – perhaps the most important and tantalizing Figure 1: NWO’s cost-effective starshade shadows the telescope from the astronomy goal for the star, while light from a terrestrial exoplanet passes the edge of the starshade coming decade. In this unimpeded. paper, we discuss the New Worlds Probe (NWP), a concept whereby we send an external occulter, known as a starshade, on its own spacecraft to work in alignment with JWST, enabling JWST to reveal those elusive habitable planets and open the search for life (Fig. 1). Recent advances in apodization functions have now enabled external occulters to be designed in a practical way for the direct detection of Earth-like planets (Cash, 2006). A starshade approximately 50 m in diameter, flying 55,000 km from a telescope can throw a sufficiently deep shadow over a telescope to reveal Earth-like planets at 1010 suppression, at as little as 75 milliarcseconds (mas) from the parent star.
    [Show full text]