The Integrated Science Instrument Module Ground Test
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Transcript of The Integrated Science Instrument Module Ground Test
The Integrated Science Instrument ModuleGround Test
Matt GreenhouseISIM Project ScientistNASA Goddard Space Flight Center23 July 2010
ISIM is the science instrument payload of the JWST
23 July 2010
The ISIM system consists of:– Four science instruments– Nine instrument support systems:
- Optical metering structure system- Electrical Harness System- Harness Radiator System- ISIM electronics compartment (IEC)- ISIM Remote Services Unit (IRSU)- Cryogenic Thermal Control System- ISIM Command and Data Handling System
(ICDH)- Flight Software System- Operations Scripts System
ISIM is one of three elements that together make up the JWST space vehicle
– Approximately 1.4 metric tons, ~20% of JWST by mass or cost
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The ISIM system completed CDR during March 2009 All science instrument ETU test programs have been completed
– All instrument ETUs have been delivered Flight model integration is underway on all instruments and supporting systems
NIRSpec Development Model NIRCam Engineering Test Unit
FGS Engineering Model MIRI Verification Model
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Making sure it all works ….
Science instruments and each of their 9 supporting systems are individually flight qualified prior to delivery to ISIM I&T
Ground testing at the ISIM element level is designed to (no order):– Verify instrument alignment with the ISIM structure– Verify instrument compatibility with the: harness system, ICDH, IRSU, FSW, & OSS– Verify design performance wrt EMI/EMC– Verify instrument compatibility with the FGS– Verify SI-to-SI compatibility for parallel mode dark calibration– Characterize thermal performance for model validation– Characterize ISIM performance stability for model validation– Correlate instrument performance in ISIM to instrument-level test results– Verify workmanship for flight environment– Measure mass properties
Approximately 200 requirements to be verified at ISIM assembly level ISIM is subsequently delivered to observatory-level I&T as a flight qualified
element
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ISIM is one of three element-level test programs
GSFC SSDIF
NG M8, M4 TVNG M8
NG M8
NG M8
GSFC SSDIF
ISIM I&T
Spacecraft Panel I&T
OTEI&T
Sunshield I&T
OTE Structure I&T
GSFC SSDIF, JSC 32
OTE/ISIM I&T
Cryo Optics Test
Spacecraft Element I&T
Facility
N/A
I&T ResponsibilityExecution
NASANGSTITTESA / Arianespace
CSG S5C, S5B, BAF, ZL3NG M8, LATF, M4 Vibe
Complete Observatory I&T
Launch Site I&T
LV Integ
Launch
NG M8
NG R8
Sunshield Pathfinders (EPF/IVA)
Observatory EM Test Bed (EMTB)
NG M8
OTE PathfinderStructure
JSC 32GSFC SSDIF
Pathfinder Optics Integration
Pathfinder Cryo Optics Test
NG M3
Propulsion Module I&T
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6Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.
The ISIM element test article (sans ICHD)
7Use or disclosure of data contained on this page is subject to the restriction(s) on the title page of this document.
ISIM Test Verification Flow
Receive Flight ISIM Electronics Compartment Structure with Backbone Harness
FLT IEC Integration(FLT E-box)
Receive Flight ISIM Structure
System Functional Test
Integrate: HAS,CHA, HR, Harness, SIs
IEC Sine & Random Vibe Test
IEC Mass Properties
DeintegrateFor Vib andMass Props ISIM Mass
Properties
Cryo Thermal Vacuum Test w/TMS and OSIM
EMI/EMCTest
Acoustics Test(ISIM & IEC)
Sine Vibe Test(ISIM Only)
Cryo Thermal Vacuum Test w/TMS and OSIM
Alignment Metrology
INS-20xxx
INS-20xxx
TST-20600 TST-20700
TST-20900 TST-21000
TST-21000
TST-20400 TST-20800 TST-21100 TST-20900
TST-21200
Clean, Inspect,Pack & Ship
TST-21300INS-21301
OTE Cryo VacAt JSC
TST-30000OTE Integration& Test Program
dI rI
dI
rI
rI – Re-Integrate ISIM and IECdI – De-Integrate ISIM and IEC
ISIM Gravity Release Test
TST-20910
ISIM will be tested at ~35 K in the GSFC SES chamber using a cryogenic telescope simulator (OSIM)
SES chamber(27 x 40 ft)
LN2 Shroud
LHe shroud
ISIM
OSIM
Vibration Isolation Supports
OSIM Primary MirrorAlignment Diagnostic Module
Fold Mirror 3 Tip/TiltGimbal Assembly
LHe shroud installation and test completed July 09
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Major ground support equipment required for ISIM I&T
Primary ground support equipment:– Cryogenic Optical Telescope Simulator (OSIM)
- Simulates Optical Telescope Element (OTE) with high fidelity– OSIM Beam Analyzer– Space environment simulator LHe shroud
- Enables ISIM testing at operating temperature– Cryogenic photogrammetry system
- Enables metrology of ISIM structure at operating temperature– ISIM Test Platform (ITP)
- Simulates OTE mechanical interface at cryogenic operating temperature ISIM simulators provided to support SI-Level testing:
– Ambient science instrument mechanical interface fixture (ASMIF)- Simulates ISIM structure mechanical interface for each instrument with high fidelity
– Science instrument test sets (SITS)- Simulates ICDH for each instrument
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The ISIM structure has passed key verification tests for cryogenic dimensional reputability and distortion
Carbon-fiber/cyanate-ester composite material– Primary launch-load bearing structure (warm launch)– High precision optical requirements
Key dimensional requirements for thermal cycling (300 to 30 K) verified to > 25 micron precision– Repeatability: 80 microns– Distortion: 500 microns
Key tests to-go:– Cryogenic and ambient strength proof tests– Modal survey
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Key Thermal Performance Test Objectives
• Best-controlled opportunity for ISIM thermal testing– 460 mW total power allocation to cryogenic portion of ISIM– Very sensitive to workmanship
• Thermal test objectives:– Thermal model correlation and validation– Workmanship/performance of critical thermal elements (heat straps,
harnesses, MLI, contamination control heaters/algorithms, trim heaters, temp sensors
– SI stability during multi-instrument operation– Sensitivity of ISIM to backplane interface temperature– MIRI thermal performance, heat load measurement within heat shield– IEC thermal balance, thermal cycling, transient stability, steady state
surface and electronics box temperatures
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ISIM enclosure and passive cryogenic radiators replaced by precision controlled cryo-pannels
Flight high purity aluminum heat strap assemblies
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Flight radiators integrated at OTIS assembly level Q meters used to verify thermal loads and flight heat strap performance MIRI cooling provided by GSE cryo-cooler compressor
IEC and Harness Radiator Flight Configuration
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The ISIM electronics compartment successfully addresses one of most difficult engineering challenges of the JWST
The IEC accommodates 11 warm electronics boxes that must reside on the cryogenic side of the sunshield close to the science instruments
Rejects ~220 W of power to space in a controlled beam pattern to achieve required observatory thermal balance and avoid thermal stray light– Radiator beam pattern verified in prototype test
Key test to-go: full thermal balance
Flight Shell Flight Baffle
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IEC & HR test shrouds simulate flight cryogenic environment with high fidelity
IEC~ 25 K Test Shroud
HR with flight harnesses
HR (~ 20 - 25 K) Shroudlined with black honeycomb
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Flight cryogenic radiators are replaced by a surrogate thermal management system
IEC Two Shroud Assembly LN2 shroud surrounded by dedicated He shroud plumbed to the primary chamber He shroud.
Harness Radiator with –V1 Shroud
Surrogate Thermal Management System (STMS) • Comprised of actively
controlled panels to produce environment of flight TMS to ISIM (Region 1)
LN2 ShroudGHe Shroud
Vibration Isolation System
Optical Telescope Element Simulator (OSIM)
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Approximately 150 optical requirements are verified or cross checked during ISIM element testing
• Only opportunity for testing integrated instrument suite with flight-like beam of flight-like image quality/wavefront
• Comprehensive optical performance test plan confirms alignment, image quality, wavefront sensing capability
OPRG1• Basic optical capabilities
OPRG2• Wavefront and focus requirements• Calibration requirements for the MIMF
wavefront sensing algorithm
OPRG3• Pupil shear and rotation requirements
OPRG4• Fields of view, vignetting, stray light• Absolute pointing of ISIM
OPRG5• Co-boresight stability vs temperture
OPRG6• Performance of NIRCam wavefront
sensing and control components
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Science Instrument (SI) sensitivity verification
SI-level requirements cover every filter and mode of the instrument
– Verified at instrument level as part of their qualification ahead of delivery to ISIM I&T- Component-level testing combined with models
Sensitivity models held under configuration control Spec values used for OTE parameters
Sensitivity benchmarks will be measured on SI internal sources during ISIM-element testing for correlation with SI-level test results
– POM contamination monitored with witness plates and NIRSpec spectroscopy on OSIM continuum sources
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JWST-RQMT-835: ISIM-153JWST Sensitivity: SN=10 in < 10,000s
Instrument
l (mm)
l/DlContinuum
Flux Density(nJy)
UnresolvedLine Flux
(10-21Wm-2)
NIRCam 2 4 11
FGS-TF 3.5 100 126
NIRSpec 3 100 132
NIRSpec 2 1000 0.52*
MIRI 10 5 700
MIRI 21 4.2 8700
MIRI 9.2 2400 10
MIRI 22.5 1200 560
* SN = 10 in < 100,000 s
Each of two cryogenic test cycles require ~20 weekswith ~ 6 weeks used for cool-down and warm-up
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Learn more at: www.jwst.nasa.gov
Watch the ISIM being built at: www.jwst.nasa.gov/webcam.html
Read about JWST science mission objectives at: http://www.jwst.nasa.gov/science.html
Collaborate on JWST science investigations:http://www.stsci.edu/institute/conference/jwst2011
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ISIM Instrument characteristics wallet card
Instrument Channel/Mode Wavelength (microns)
Typical Spectral Resolution (l/Dl) FOV
Angular Resolution (arc sec)
Number of Sensor Chip
Arrays
Mega Pixels Detector Type / Format NIR=18 um pixels MIR=25 um pixels
Detector Temp (K)
Shortwave 0.6 - 2.3 4,10,100 2.2' x 2.2' each of 2 modules 0.032 / pixel 8 34 HgCdTe / 2048 x 2048 40Longwave 2.4 - 5.0 4,10,100 2.2' x 2.2' each of 2 modules 0.065 / pixel 2 8 HgCdTe / 2048 x 2048 40
1.0 - 5.0 1000
0.6 - 5.0 100see FOV
IFU 0.7 - 5.0 2700 3 x 3 arc-sec 0.10 slice widthImager 5 - 27 4-6 1.9' x 1.4' 0.11 / pixel 1 1 Si:As / 1024 x 1024 7Low Res Slit 5 - 11 100 5" x 0.6" see FOV 1 1 Si:As / 1024 x 1024 7
4.87 - 7.76 3000 3.7" x 3.7" 0.18 slice widthMed Res IFU 7.45 - 11.87 3000 4.7" x 4.5" 0.28 slice width 1 1 Si:As / 1024 x 1024 7
11.47 - 18.24 3000 6.2" x 6.1" 0.39 slice width17.54 - 28.82 2250 7.1" x 7.7" 0.65 slice width
FGS-TF 1.6 - 2.5, 3.2 - 4.9 100 2.2' x 2.2' 0.065 / pixel 1 4 HgCdTe / 2048 x 2048 40FGS-Guider 0.8 - 5.0 0.7 2.3' x 2.3' each of 2 modules 0.068 / pixel 2 8 HgCdTe / 2048 x 2048 40
Total ISIM 66
Wavelength (microns)
Instrument/Mode Bandwidth (l/Dl)
SNR Maximum Wall Clock Time (s)
2 NIRCam 4 10 10,000 11.40 0.11 NA3.5 FGS-TF 100 10 10,000 126.00 1.26 NA3 NIRSpec/Low Res 100 10 10,000 132.00 1.32 NA2 NIRSpec/ Med Res NA 10 100,000 NA NA 0.57
10 MIRI/ Broadband 5 10 10,000 700.00 7.00 NA21 MIRI/Broadband 4.2 10 10,000 8700.00 87.00 NA9.2 MIRI/Spectrometer 2400 10 10,000 NA NA 1022.5 MIRI/Spectrtometer 1200 10 10,000 NA NA 56.00
Instrument Mass: Region 1/2 Volume Observation Power Uncompressed Data Volume Flight Item PDR CDR Flt Delivery
(kg) R1 (m3) Region 2 (W) (Gbits / day) NIRCam Oct-04 May-06 Mar-10NIRCam 161 / 46 ~0.3 52 334 NIRSpec Dec-05 Oct-08 Nov-09NIRSpec 220 / 44 ~3.5 40 232 MIRI OBA Mar-05 Dec-06 Feb-10MIRI 102 / 33 ~2.5 37 96 MIRI Cryo-Cooler Feb-08 Dec-08 Jan-11FGS 92 / 21 ~0.6 51 68 FGS-Guider May-05 Mar-07 Mau 10Total SI 575 / 144 180 FGS-TF May-05 Mar-08 May-10
Total ISIM 1065 / 340 200 ISIM Oct-06 Nov-08 Sep-11SI/ISIM 0.54 / 0.42 0.90 NA
ISIM Fast Facts
37
Schedule (ISIM Rev-F)
8 HgCdTe / 2048 x 20482
Unresolved Line Flux
(10-21 W m-2)
Long Slits (5) 1.0 - 5.0 100, 1000, 2700200 x 3500 mas x 3, 400 x 4000 mas, 100 x 2000 mas
K ey Instrument Charac teristics (as of Mar 06)
NIRCam
NIRSpec
203 x 463 mas clear shutter aperture, 267 x 528 mas pitch, 4 x 171 x 365 shutter array format, 9.7 sq arcmin mulit-object targetable solid angle
Multi-Object Spec
Greenhouse: Update: March 08
J WST Sensitivity (JWST-RQMT-000634 Rev-M Baseline)
Resource Allocations (as of May 07)
MIRI
Continuum Flux Density
(nJy)
Continuum Flux Density
(10-33 W m -2 Hz-1)
max ISIM = 458 (NIRCam prime, NIRSpec parallel cal 24% utilization
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NIRCam will provide the deepest near-infrared images ever and will identify primeval galaxy targets for the NIRSpec
Developed by the University of Arizona with Lockheed Martin ATC– Operating wavelength: 0.6 – 5.0 microns – Spectral resolution: 4, 10, 100– Field of view: 2.2 x 4.4 arc minutes– Angular resolution (1 pixel): 32 mas < 2.3 microns, 65 mas > 2.4 microns– Detector type: HgCdTe, 2048 x 2048 pixel format, 10 detectors, 40 K passive cooling– Refractive optics, Beryllium structure
Supports OTE wavefront sensing
Coronagraph Elements
Dichroic Beamsplitter
Collimator Triplet Subassembly
First Fold Mirror Subassembly
Shortwave Filter Wheel Assembly Elements
Shortwave Triplet Subassembly
Shortwave Fold Mirror
Pupil Imaging Lens
Shortwave Focal Plane Housing Fold Mirror
Longwave Focal Plane Housing Fold Mirror
Longwave Triplet Subassembly
Longwave Filter Wheel Assembly Elements
Pick-off Mirror Subassembly
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The NIRSpec will aquire spectra of up to 100 galaxies in a single exposure
Developed by the European Space Technology Center (ESTEC) with Astrium GmbH and Goddard Space Flight Ctr
– Operating wavelength: 0.6 – 5.0 microns– Spectral resolution: 100, 1000, 3000– Field of view: 3.4 x 3.4 arc minutes
- Aperture control: programmable micro-shutters, 250,000 pixels
- Angular resolution: shutter open area 203 x 463 mas, pitch 267 x 528 mas
– Detector type: HgCdTe, 2048 x 2048 pixel format, 2 detectors, 37 K passive cooling
– Reflective optics, SiC structure and optics
MIcro-shutterArray
(f/12.5) Collimator
Prism/GratingWheel
CameraDetector
Array(f/5.67)
Telescope Focus (f/20)
Foreoptics
FilterWheel
Pick-off Mirror(s)
3.6’
3.4’
Detector Array
Fixed Slits and
IFU Aperture
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Aperture control: 250, 000 programmable micro-shuttersSystem at TRL-8 and delivered to ESA June 2010
Human Hair 90 um Dia.
203 x 463 mas shutter pixel clear aperture, 267 x 528 mas pitch, 4 x 171 x 365 array
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The MIRI instrument will detect key discriminators that distinguish the earliest state of galaxy evolution from more evolved objects
Developed by a European Consortium and JPL– Operating wavelength: 5 - 29 microns– Spectral resolution: 5, 100, 2000– Field of view: 1.9 x 1.4 arc minutes broad-band imagery
- R100 spectroscopy 5 x 0.2 arc sec slit- R2000 spectroscopy 3.5 x 3.5 and 7 x 7 arc sec integral field units
– Detector type: Si:As, 1024 x 1024 pixel format, 3 detectors, 7 K cryo-cooler– Reflective optics, Aluminum structure and optics
Optical Assembly Structural/Thermal Model
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Developed by the Canadian Space Agency with ComDev– Operating wavelength: 0.8 – 4.8 microns– Spectral resolution: Broad-band guider and R=100 science imagery– Field of view: 2.3 x 2.3 arc minutes
- R=100 imagery with Fabry-Perot tunable filter and coronagraph– Angular resolution (1 pixel): 68 mas– Detector type: HgCdTe, 2048 x 2048 pixel format, 3 detectors – Reflective optics, Aluminum structure and optics
The FGS provides imagery for telescope pointing control & imaging spectroscopy to reveal primeval galaxies and extra-solar planets
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