DOCSLIB.ORG

JWST Project Status

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
JWST Project Status James Webb Space Telescope JSTUC Project Status June 8, 2020 29 July 2011 11 Topics Project Status Observatory I&T Ground System and Operations Launch Vehicle Commissioning 2 Observatory Status 3 Observatory Major Accomplishments Completed Deployment Tower Assembly (DTA) deployment/stow (#1) Completed Sunshield Deployment Completed Sunshield Membrane Folding Completed anomalous Command/Telemetry Processor (CTP) and Traveling Wave Tube Amplifier (TWTA) replacements Root cause for both anomalous flight boxes identified – both random part failures which don’t impugn other units Deployed/Stowed Primary Mirror Wings as part of Observatory Pre- Environmental Deployments MIRI Cryocooler Fill Complete Sunshield (SS) Bi-Pod First Motion Test Successfully Complete DTA Deployment (#2) Complete Partial Stow SS Unitized Pallet Structure Complete 4 TWTA and CTP Replacement 5 Deployed Primary Mirror 6 Sunshield Preps For Folding 7 Remaining I&T Activities Spacecraft Elem. Observatory Observatory Post-environmental Pre-environmental Environmental Deployments Deployments Tests Completed In Progress Begins in Aug. Observatory Observatory Post-environmental Deployments Final Build 8 Remaining I&T Activities SCE Post SCE OTIS/SCE / Environment Reconfigure Deployments SCE for OTIS Integration OTIS Integration (Part 1) 2 DTA Deploy Sunshield Sunshield Fold J2 Panel Stow Deployment Sunshield Preps for Repairs & Sunshield Stow DTA #1 Opening Midbooms #1 Membranes Folding Updates Membranes Propulsion SCE Post-Env MRD Install GAA ROM SCE Deployment Part Test Cryocooler Bi-pod Preps Bipod DTA Install 4-bar/ Field Joint Partial Stow Deploy Wings Stow Wings & Release Deployment J3 Panel Stow DTA #2 Mate, UPS Full Stow UPS 1st Motion #2 MRDs OTIS IEC Env Deployment - OBS Closeout LL DTA Cable Full Stow UPS CST4 / GSEG3 Operations Tray OBS Pre Move OBS to Acoustic Move OBS to Move OBS to Vibe Testing LATF Testing M4 M8 OBS Env Test DTA Deploy Fold GAA, CCA, Stow Deploy UPS Deployment Sunshield Stow Core Sunshield CST5 / GSEG4 Stow DTA #3 STSA Release Midbooms #3 Membranes Membranes Env Deployments - IEC, CJAA, DTA Install 4-bar/ Partial Stow Final Stow LL DTA Cable Deploy Wings ADIR +V3 Stow Wings Deployment J3 Panel Full Stow UPS UPS DTA #4 Tray Release #4 MRDs OBS Post OBS Ready to Shipping Final OBS Ops Ship to Slack to Ship to Launch Preps Launch OBS Final Build Final OBS 9 Ground System Status 10 JWST Ground Segment and Operations All systems required for both Science and Mission Operations are complete Science and Operations Center (S&OC) running Release 2.1, delivered in April 2020 Preparing to support interface testing between the S&OC and the Observatory (GSEG- 3) in July 2020 Work continues (even in the current environment) on discrepancy report fixes, enhancements and requirements verification Flight Operations Team is fully staffed and all operational products are essentially complete with “tweaks” being made based on testing, mission rehearsals, and contingency planning Mission Rehearsals The most recent rehearsals, Early Commissioning Exercise #4 and Contingency Planning Rehearsal 4, were completed in February 2020 Strategies for formal rehearsal campaign (Launch Readiness Exercises, Integrated Crew Exercises, Mission Dress Rehearsal) are being worked to account for current COVID protocols 11 Rocket and Launch Site Status 12 Rocket and Shipping to Launch Site LV mechanical qualification complete, GNC qualification nearing completion SQR planned end of June; JWST Qualification-Certificate to be signed in Aug. Rocket Hardware Fairing customization design & mfg., and qualification review complete • Demo flight with full customization scheduled for late July (TBR) Standard rocket components in various stages of manufacturing as a “batch” “Cherry Picking” of JWST specific components starts approximately 1 year prior to launch Chartered ocean vessel – Port of Long Beach to Kourou sea port for shipping JWST to launch site NASA has leveraged the US Transportation Command to ensure the safest and most secure transport possible. 13 At The Launch Site Complexity of JWST presents challenges to any remote operation and launching from CSG presents even further challenges due to its uniqueness Last NASA launch out of CSG in early 90’s Logistics getting to and operating at CSG adds complexity Launch Site preps begin long before JWST arrives ~ 300-400 tasks need to be completed before we arrive at CSG • Range anywhere from developing procedures to building a contamination system which will be brought to CSG • All task are on milestone based schedule and monitored weekly At the launch site ~ 800 tasks must be completed prior to launch • Includes electrical testing, communication testing, etc. • All tasks are reviewed regularly to look for efficiencies, etc. 14 At The Launch Site Launch site operations have been slowed during the Covid-19 phase of the effort but significant work has been enabled to continue Launch Site Readiness HEPA Filter build and performance testing has started at GSFC Laser Radar calibration and preparation for shipment to Nelson Engineering in Ohio to support JWST transporter proof testing has started at GSFC. Launch site technical risk has been reduced with improvements in the flow which eliminate significant complexity in the Observatory processing. For example, simplification of contamination control, elimination of the need to remove and reinstall the SA, minimizing lifts of JWST, etc. At the launch site JWST is at the launch site for ~ 72 days with the Observatory present for 65 days. NASA and NGAS staffing at Launch site finalized. 15 Launch Site Work at GSFC during Phase 4 HEPA Filter Build-Up at GSFC Laser Radar Calibration at GSFC 16 On-Orbit Commissioning 17 Commissioning Planning Status • Commissioning Overview • 180 day time allocation • 30 days for launch, spacecraft activation, mid-course corrections, and deployment • 91 days for cool down, telescope phasing, and activation of instruments and cryo-cooler • 59 days for science instrument calibrations • Commissioning Organization • Established activity based Commissioning team organization • Each on-orbit activity has a specific responsible engineer to insure I&T hardware behavior, flight operational products, and nominal and contingency plans are consistent and complete. • Established key systems engineering positions • Spacecraft Commissioning phase lead and Cool Down/OTIS phase lead • Examples of Technical and Risk Reduction Activities • Updated timeline and activities in support of time critical mid-course correction maneuvers • Full review of all hardware test behavior, failures, etc. for any impact on flight operations nominal and contingency planning • Enhanced spacecraft attitude control system capabilities to spin/shake observatory to support any significant deployment anomalies • Completed full commissioning timeline review to synchronize with final correlated model predictions for cool down and contamination heater control • Completed assessment of deployment order to determine if updates needed. • Updated Sunshield tensioning sequence – reduces possibility of slack/loose cables • Investigated early deployment of secondary mirror – only used in contingency plan • Investigated swapping +-J2 Sunshield mid booms to achieve more benign antenna gimbal temperatures – only used in contingency planning 18 Commissioning Planning Status – cont. Commissioning Reviews….. Completed a very detailed of series of internal audits with entire Commissioning Team • April 20-23 – Spacecraft Commissioning (Launch and Ascent, Mid-Course Corrections, Spacecraft Subsystem Activation and Checkout • April 28-30 – Wavefront Control/Line of Site (Attitude Control and Fine Guiding) • May 12-14 – ISIM Systems, Cooler, Cool-Down Audit utilized internal review team with tracked findings and actions Commissioning planning is extremely mature and audit findings are being used to finalize and prioritize work and planning priorities, Deployments activity audit planned for August…will utilize external peer review team consisting of outside deployment experts. System Roll up review planning has started. Will summarize audits and focus on system level Commissioning activities, Contingency Planning Contingency planning status was reviewed as part of audits. Currently focused on completely contingency response flows for all deployments for project office review and approval. 19 Conclusion JWST has been making excellent progress From the period of early December through early March execution schedule was maintained without using any schedule reserve Activities across JWST are being impacted and are being fully assessed along with a preplanned Schedule Risk Assessment 20.
Load more

Recommended publications
  • The James Webb Space Telescope
    The James Webb Space Telescope Jonathan P. Gardner NASA’s Goddard Space Flight Center http://jwst.nasa.gov Space Science Reviews, 2006, 123/4, 485 1 James Webb Space Telescope Integrated Science Primary Mirror Instrument Module (ISIM) • 6.6m Telescope • Successor to Hubble & Spitzer. • Demonstrator of deployed optics. Secondary • 4 instruments: 0.6 to 28.5 μm Mirror • Passively cooled to < 50 K. • Named for 2nd NASA Administrator 5 Layer Sunshield Spacecraft Bus • Complementary: 30m, ALMA, WFIRST, LSST • NASA + ESA + CSA: 14 countries • Lead: Goddard Space Flight Center • Prime: Northrop Grumman • Operations: STScI • Senior Project Scientist: Nobel Laureate John Mather • Launch date: October 2018 2 NIRCam: NIRSpec Imaging 0.6 – 5.0 µm Broad, med & narrow 10 sq. arcmin FOV 65 mas resolution Coronagraphy NIRCam FGS/NIRISS: NIRSpec: Guiding Multi-object: 10 sq. arcmin Slitless spectroscopy (R~150) IFU: 3x3 arcsec Exoplanet transits (R~750) R~100, R~1000, R~3000 Non-redundant mask MIRI: 5 – 28.5 µm 2 sq. arcmin FOV IFU R~3000 Coronagraphy FGS/NIRISS MIRI 4 Model-Dependent Rule of Thumb: Deep NIR Surveys • Ultra-deep, deep and deep-wide imaging surveys: • JWST will do at z~12 what HST is doing at z~6 • JWST will do at z~17 what HST is doing at z~9 CANDELS UDF COSMOS 5 15 Angular Resolution 2 mm 10 5 per 1 kpc 3.6 mm NIRCam Pixels 0 0 10 20 Redshift NIRCam resolution JWST + NIRCam have enough resolution to study the structure of distant galaxies. The plots at right show the two-pixel resolution at 2 microns.
    [Show full text]
  • NASA Next Editor at the Gas Giant, Orbiting Jupiter 37 Core
    MAY 2016 1 NASAnext National Aeronautics and Space Administration next NASAempowering the next generation of space explorers OSIRIS-REx NASA’s asteroid sampling mission takes off PAGE 6 www.nasa.gov MAY 2016 MAY 2016 2 3 NASAnext NASAnext Dear Reader, Humans are curious; they love to explore. Throughout our history, man has tirelessly pursued the next hori- zon. The same is true of our scientists and engineers. NASA’s missions and accomplish- ments are a direct result of this ines- capable curiosity and thirst for explo- ration. To many of our scientists and engineers, space is the final frontier — a place of endless discovery. Our eyes are fixed on this frontier. NASA’s Hubble Space Telescope has helped scientists uncover some of the most distant objects ever seen. We observed the Juno spacecraft make A meteor streaks across the sky during the annual Perseid meteor shower on Aug. its arrival at Jupiter this summer. In 12, 2016, in West Virginia. What have you seen in the night sky? NASA/Bill Ingalls fall, we watch as OSIRIS-REx trav- els to a near-Earth asteroid known as Bennu to retrieve a sample and send it back to Earth. SEPTEMBER 2016 But our scientists and engineers juno know that we also must keep a close meets a 3 Juno meets a giant eye on our own planet. Warmer than NASA/JPL-Caltech average temperatures and disappear- ing sea ice are indicators that our 4 NASA’s NICER planet is changing. NASA continuous- ly monitors and studies these chang- giant 5 One planet, two suns es to help us understand the future of upiter has captivated people sky, Jupiter’s magnetic field would ap- our home.
    [Show full text]
  • James Webb Space Telescope
    Integrated Science Instrument Module NASA’s Goddard Space Flight Center Optical Telescope Element Mid-infrared Instrument NASA/JPL, ESA Telescope Design and Deployment Near-infrared Spectrograph Northrop Grumman European Space Agency (ESA) Optical Telescope and Mirror Near-infrared Camera Design University of Arizona Ball Aerospace Fine Guidance Sensor Telescope Structures Canadian Space Agency Alliant Techsystems James Optical Telescope Integration and Test ITT/Exelis Webb Mirror Manufacturing Beryllium Mirror Blanks Brush Wellman Space Mirror Machining Axsys Technologies For more information, please contact: Telescope Mirror Grinding and Polishing SSG/Tinsley Laboratories Northrop Grumman Aerospace Systems Blake Bullock Milestone 310-813-8410 Achievements [email protected] in 2012 Christina Thompson 310-812-2375 [email protected] Spacecraft Bus Northrop Grumman Sunshield Northrop Grumman ManTech/NeXolve Webb Telescope Operating in space nearly a million miles from Earth and protected by its tennis court-sized, five-layer sunshield, the Webb Telescope will be shielded from sunlight and kept cool at a temperature of approximately www.northropgrumman.com 45 Kelvin (-380° F). This extreme cold enables Webb’s infrared © 2012 Northrop Grumman Systems Corporation Printed in USA sensors to see the most distant galaxies and to peer through galactic CBS Bethpage dust into dense clouds where star and galaxy formation take place. 12-2339 • AS • 12/12 • 43998-12 Northrop Grumman is under contract to NASA’s Goddard Space Flight Center in Greenbelt, Md., for the design and development of the Webb Telescope’s optics, sunshield and spacecraft. James Webb Space Telescope assembly is a critical component of the spacecraft that closes the Webb’s Far-reaching Achievements in 2012 mission data link to NASA’s Deep Space Network that will transmit the he James Webb Space Telescope is NASA’s top science mission telescope’s data from its orbit nearly a million miles from Earth.
    [Show full text]
  • James Webb Space Telescope | Handbook James Webb Space Telescope | Handbook
    James Webb Space Telescope | Handbook James Webb Space Telescope | Handbook Contents 1. Introduction 2 2. Design 3 2.1 Development timeline 3 2.2 Testing 4 2.3 Sunshield 4 2.4 Mirror 6 2.5 Instruments 7 3. Mission 9 3.1 Infrared light 9 3.2 First light 10 3.3 Formation and evolution of galaxies 11 3.4 Formation of stars and planetary systems 12 3.5 Planetary systems and the origins of life 12 4. Taking Webb into schools 13 5. Glossary 14 6. Useful links 15 Note: numbers in square brackets, e.g. [1] refer to entries in the glossary. James Webb Space Telescope | Handbook 1. Introduction This guide contains information about the James Webb Space Telescope. Webb is a collaboration between ESA, NASA, and the Canadian Space Agency. It is named after the NASA administrator James E. Webb who oversaw the first human spaceflight programmes of Mercury and Gemini and the establishment of the Apollo missions. Webb is the largest space telescope ever built and it will see objects up to 100 times fainter than those the Hubble Space Telescope can see. Hubble observes mainly visible light but Webb will use infrared light. Infrared light allows scientists to see further back in time to when the earliest stars and galaxies formed and into areas where visible light cannot get through, such as clouds of gas where stars and planets form. Scientists will use these observations to understand as much as possible about how the Universe evolved into what is seen today. Thousands of engineers and scientists from across the world have worked together for over twenty years to design and develop the technologies required for such a large and complex telescope.
    [Show full text]
  • JWST OTE and OTIS Review
    Telescope, ISIM, Spacecraft & Observatory Development ======================= - Pictorial History - Gary Matthews Chris Gunn 1 JWST OTE and OTIS Review • Acronym Review • OTE – Optical Telescope Element – The Telescope • ISIM – Integrated Science Instrument Module • OTIS – OTE/ISIM Integrated Subsystem – The Camera – Payload • SCE – Spacecraft Element • Current Status • The OTE/ISIM – OTIS are now part of an Observatory at NGAS 2019 Mirror Tech Days – JWST OTE Review 2 Hardware Timeline 2012 2014 2015 2016 SSDIF Pathfinder OTIS OTIS OTE Optical OTE/ISIM OTIS Vibe Cleanroom Optical Thermal Acoustic Integration Integration Test Preps Integration Closeouts Test Pathfinder OTE Optical Optical Integration 2017 Integration JSC Cleanroom Cryo Final OTIS OGSE1 OGSE2 Thermal & Chamber Load Chamber Cryo (CoC Only) (BIA) Pathfinder Preps Test Cert Test 2018 here are We Ship SCE/OTIS To NGAS I&T 3 - 2012 - Before we can start SSDIF and JSC Facility Modifications 2019 Mirror Tech Days – JWST OTE Review 4 SSDIF* pre-OTE SSDIF before JWST Hubble stuff all over the place Pre-ISIM and OTE * Spacecraft Systems Development and Integration Facility 2019 Mirror Tech Days – JWST OTE Review 5 AOAS* Installation in SSDIF Need finished picture *Ambient Optical Alignment Stand 2019 Mirror Tech Days – JWST OTE Review 6 OTE Integration Equipment PAIF placing primary mirror system assembly (PMSA) onto the Backplane Stability Thermal Assembly (BSTA) AOAS in the GSFC Cleanroom 2019 Mirror Tech Days – JWST OTE Review 7 Pre-JWST view of the JSC vacuum chamber A lot of potential stuff here. Your discretion The transformation As we arrived – The original chamber. Before the clean room Clean room installation The Harris upgrades.
    [Show full text]
  • Cooling Technology for Large Space Telescopes
    Source of Acquisition NASA Goddard Space Flight Center Cooling Technology for Large Space Telescopes Michael DiPirro, Paul Cleveland****, Dale Durand*, Andy Klavins*", Danniella Muheim, Christopher Pahe***, Mike Petach*, Domenick Tenerelli*", Jason Tolomeo**, Keith Walyus NASA Goddard Space Flight Center; Greenbelt, MD 20771 * Northrop Grumman Space Technology; One Space Park; Redondo Beach, CA 90278 ** Lockheed Martin Space Systems Company; 1111 Lockheed Martin Way; Sunnyvale, CA 94089 *** Jet hopulsion Laboratory; California Institute of Technology; 4800 Oak Grove Drive; Pasadena, CA 91 109 **** Energy Solutions International, LLC, 8705 Cathedral Way, Gaithersburg, MD 20879-1791 Abstract - NASA's New Millennium Program funded an effort to incompatible with the design and lifetime requirements of develop a system cooling technology, which is applicable to all large far-infrared (IR) observatories: they are large, cumber- future infrared, sub-millimeter and millimeter cryogenic space some to incorporate into an observatory, require special telescopes. In particular, this technology is necessary for the launch and early operations procedures, and ultimately limit proposed large space telescope Single Aperture Far-Infrared Telescope (SAFIR) mission. This technology will also enhance the useful lifetime of the instruments. The new paradigm for the performance and lower the risk and cost for other cryogenic cooling to low temperatures will be cryogen free. It will in- missions. The new paradigm for cooling to low temperatures volve passive cooling using light-weight deployable mem- will involve passive cooling using lightweight deployable mem- branes that serve both as sunshields and V-groove radiators, branes that serve both as sunshields and V-groove radiators, in in combination with active cryogenic coolers providing tem- combination with active cooling using mechanical coolers oper- peratures down to 4 K.
    [Show full text]
  • NASA Goddard Space Flight Center, Greenbelt, MD
    THERMAL-STRUCTURAL ANALYSIS OF SUNSHIELD MEMBRANES John Johnston and Keith Parrish NASA Goddard Space Flight Center, Greenbelt, MD Abstract reference mission consisting of multiple-layers of diamond-shaped, thin-film membranes supported by Future large infrared space telescopes, such as the four deployable booms arranged in a cruciform manner. James Webb Space Telescope (JWST), will require Membrane management hardware at the interface deployable sunshields to provide passive cooling for between the booms and films positions and tensions the optics and instruments. Deployable sunshield structures films. The pre-tensioning forces must be adequate to for such applications typically consist of multiple thin- maintain desired film flatness and spacing, as well as to film membrane layers supported by deployable booms. , accommodate thermal strain effects. Relatively small The mechanical design of the sunshield must preload forces (on the order of 10 N per corner) were accommodate thermal strains due to layer-to-layer baselined in the NASA reference concept sunshield in temperature differences as well as potentially large in- order to reduce compressive loads on the deployment plane temperature gradients within individual film booms to help minimize the overall structural mass. layers. This paper describes a thermal-structural Lower film stresses also reduce the risks of tear analysis for predicting the stress state in a thin-film propagation and the effects of creep. The selection of membrane subject to both mechanical thermal loads low preload forces does however result in several less that could aid in the mechanical design of future desirable effects, including increased errors in film sunshield structures. First the temperature field positioning, increased film wrinkling, and low predicted by a thermal analysis is mapped to a frequency film dynamics.
    [Show full text]
  • L3harris James Webb Space Telescope (JWST)
    JAMES WEBB SPACE TELESCOPE (JWST) JWST is a space-based observatory that will provide unprecedented images of the universe’s first stars and galaxies. L3Harris is playing an important role in the assembly, integration and testing of the telescope. L3HARRIS’ ROLE JWST MISSION DETAILS: As part of the NASA team, L3Harris As the successor to the Hubble Space > Mission duration is 5-10 years integrated components made by various Telescope, JWST is slated for launch > Diameter of primary mirror is partners to form the Optical Telescope in 2021 and will take three months to approximately 6.5 meters, Element, which will collect light and travel 1.5 million kilometers (940,000 or 21.3 feet provide sharp images of deep space. miles) to a point in space where it will L3Harris also combined the components be balanced between the gravity of the > Primary mirror consists of the Integrated Science Instrument Earth and the sun. JWST is a large, of 18 segments Module, which hosts four cameras infrared-optimized telescope designed > Primary mirror segments are and spectrographs for gathering data. to study the formation of the first stars made of beryllium and coated L3Harris later administered about 100 and galaxies, the evolution of galaxies, with gold days of testing in a cryogenic vacuum the production of elements by stars and chamber at Johnson Space Center to the process of star and planet forma- ensure the telescope elements perform tion. JWST will be located much farther in the harsh environment found in space. from Earth than Hubble and will contain a tennis court-sized sun shade that will keep the telescope cold, which is neces- sary for viewing infrared light.
    [Show full text]
  • The MIRI Coronagraphs
    The Mid-Infrared Instrument for the James Webb Space Telescope, V: Predicted Performance of the MIRI Coronagraphs A. Boccaletti1, P.-O. Lagage2, P. Baudoz1,C.Beichman3.4.5,P.Bouchet2,C.Cavarroc6,D. Dubreuil2, Alistair Glasse7,A.M.Glauser8,D.C.Hines9, C.-P. Lajoie9, J. Lebreton3,4,M. D. Perrin9,L.Pueyo9,J.M.Reess1,G.H.Rieke10, S. Ronayette2,D.Rouan1,R. Soummer9, and G. S. Wright7 ABSTRACT The imaging channel on the Mid-Infrared Instrument (MIRI) is equipped with four coronagraphs that provide high contrast imaging capabilities for studying faint point sources and extended emission that would otherwise be overwhelmed by a bright point-source in its vicinity. Such bright sources might include stars that are orbited by exoplanets and circumstellar material, mass-loss envelopes around post-main-sequence stars, the near-nuclear environments in active galax- ies, and the host galaxies of distant quasars. This paper describes the coron- agraphic observing modes of MIRI, as well as performance estimates based on measurements of the MIRI flight model during cryo-vacuum testing. A brief 1LESIA, Observatoire de Paris-Meudon, CNRS, Universit´e Pierre et Marie Curie, Universit´eParis Diderot, 5 Place Jules Janssen, F-92195 Meudon, France 2Laboratoire AIM Paris-Saclay, CEA-IRFU/SAp, CNRS, Universit´e Paris Diderot, F-91191 Gif-sur- Yvette, France 3Infrared Processing and Analysis Center, California Institute of Technology, Pasadena, CA 91125, USA 4NASA Exoplanet Science Institute, California Institute of Technology, 770 S. Wilson Ave., Pasadena, CA 91125, USA 5Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Dr., Pasadena, CA 91107, USA 6Laboratoire AIM Paris-Saclay, CEA-IRFU/SAp, CNRS, Universit´e Paris Diderot, F-91191 Gif-sur- Yvette, France 7UK Astronomy Technology Centre, STFC, Royal Observatory Edinburgh, Blackford Hill, Edinburgh EH9 3HJ, UK 8ETH Zurich, Institute for Astronomy, Wolfgang-Pauli-Str.
    [Show full text]
  • The Mid-Infrared Instrument for JWST
    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, V: Predicted Performance of the MIRI Coronagraphs A. Boccaletti1, P.-O. Lagage2, P. Baudoz1,C.Beichman3.4.5,P.Bouchet2,C.Cavarroc6,D. Dubreuil2, Alistair Glasse7,A.M.Glauser8,D.C.Hines9, C.-P. Lajoie9, J. Lebreton3,4,M. D. Perrin9,L.Pueyo9,J.M.Reess1,G.H.Rieke10, S. Ronayette2,D.Rouan1,R. Soummer9, and G. S. Wright7 ABSTRACT The imaging channel on the Mid-Infrared Instrument (MIRI) is equipped with four coronagraphs that provide high contrast imaging capabilities for studying faint point sources and extended emission that would otherwise be overwhelmed by a bright point-source in its vicinity. Such bright sources might include stars that are orbited by exoplanets and circumstellar material, mass-loss envelopes around post-main-sequence stars, the near-nuclear environments in active galax- ies, and the host galaxies of distant quasars. This paper describes the coron- agraphic observing modes of MIRI, as well as performance estimates based on measurements of the MIRI flight model during cryo-vacuum testing. A brief 1LESIA, Observatoire de Paris-Meudon, CNRS, Universit´e Pierre et Marie Curie, Universit´eParis Diderot, 5 Place Jules Janssen, F-92195 Meudon, France 2Laboratoire AIM Paris-Saclay, CEA-IRFU/SAp, CNRS, Universit´e Paris Diderot, F-91191 Gif-sur- Yvette, France 3Infrared Processing and Analysis Center, California Institute of Technology, Pasadena, CA 91125, USA 4NASA Exoplanet Science Institute, California Institute of Technology, 770 S.
    [Show full text]
  • James Webb Space Telescope Thermal Pathfinder Test Development
    46th International Conference on Environmental Systems ICES-2016-429 10-14 July 2016, Vienna, Austria James Webb Space Telescope Thermal Pathfinder Test Development Angelique Davis1 Edge Space Systems, Glenelg, MD 21737 Wes Ousley2 and William Burt3 Genesis Engineering Solutions, Lanham, MD, 20706 Christine Cottingham4 Edge Space Systems, Glenelg, MD 21737 The James Webb Space Telescope (JWST), scheduled for launch in 2018, includes a 6m primary mirror passively cooled below 55 Kelvin. The observatory cannot be optically or thermally tested as a system at flight temperatures due to its large sunshield, so the telescope portion along with its instrument complement will be tested as a single unit. This test is scheduled for 2017, and on the program schedule critical path, so a set of cryogenic tests with some flight-like hardware is being performed earlier to help mitigate this schedule risk. This paper updates plans and associated thermal analysis for the 2016 JWST Thermal Pathfinder (TPF) cryogenic test. The primary TPF test objective is to run the flight telescope test cooldown timeline with a thermally similar Pathfinder configuration. Thermal hardware was added to the Pathfinder structure to more closely match telescope thermal characteristics, including flight-like insulation and blanks to simulate most mirrors. Another TPF thermal objective is to provide insight into flight backplane heat flow characteristics, which are critical for accurate flight predictions. Other hardware will be in the chamber for TPF as a dry run for the flight telescope test and to provide the proper thermal environment, including a simulator for the warm spacecraft, support structures, thermal targets, and a sunshield simulator.
    [Show full text]
  • 19760022256.Pdf
    NASA TECHNICAL NASA TM x-73073 MEMORANDUM 0 roSKYLAB LESSONS LEARNED AS APPLICABLE TO A LARGE SPACE STATION William C. Schneider Office Of Space Flight Headquarters NASA April 1976 Report On Period 1967-1974 National Aeronautics And Space Administration Washington, D. C. 20546 .76-293 4 _ ~SyyJAB LESSONS LanD - ., - X-373) _ I,, sTATION, (-&ASA-M- O A LARGE SIACB . Uiv. of JnclaS AP tIcABLEpfl Thesis pr6- 97 Ph.D. T e~ - CatholiC CSC 223 3 1 48953 1 (ASA) 286 P HC $9.25 C 9 AM 28 ?324 %C 197, P' S INDEX SUMMARY I INTRODUCTION 3 PURPOSE AND SCOPE OF PAPER 3 GENERAL DESCRIPTION 3 HISTORY OF SKYLAB 21 MISSION SUMMARY 35 SKYLAB LESSONS LEARNED 74 INTRODUCTION 74 LESSONS LEARNED 75 COMMENTS BY SKYLAB OFFICIALS 120 INTRODUCTION 120 COMMENTS 120 LETTERS 130 AXIOMS 173 CONCLUS IONS 174 ACRONYMS 177 APPENDIX I - HA-RDWARE DESCRIPTION 178 APPRENIX II - EXPERIMENT DESCRIPTION 217 REFERENCES 279 BIBLOGRAPHY 282 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TMX-73073 4. Title and Subtitle 5. Report Date April 1976 Skylab Lessons Learned As Applicable To A Large 6. Performing Organization Code Space Station 7. Author(si 8. Performing Organization Report No. William C. Schneider 10. Work Unit No. 9. Performing Organization Name and Address NASA Headquarters, Office of Space Flight 11 Contrac or Grant No. 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Technical Memorandum pTQr7- g7a) National Aeronautics and Space Administration 14. Sponsoring Agency Code Washington, D.C. 20546 15. Supplementary Notes Report prepared for variety of purposes; History records; reference; training; dissertation for Doctoral Thesis at Catholic University of America.
    [Show full text]