Presented to: The LUVOIR STDT Matthew R. Bolcar April 17, 2017 · 4/17/2017 · IDC Study Schedule...
Transcript of Presented to: The LUVOIR STDT Matthew R. Bolcar April 17, 2017 · 4/17/2017 · IDC Study Schedule...
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Presented to: The LUVOIR STDT Matthew R. Bolcar April 17, 2017
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Matt’s Laptop at about 6pm yesterday
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Matt’s Laptop at about 6pm yesterday
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SSD
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We will study two architectures in depth... � Architecture A (first half of 2017)
� 15-m diameter aperture � Four instrument bays:
○ Optical / NIR Coronagraph (A) ○ UV Multi-object Spectrograph (“LUMOS”) ○ High-definition Imager (will also perform guiding / wavefront sensing) ○ Pollux: UV Spectro-polarimeter and High-Resolution Spectrograph
(CNES Contributed)
� Architecture B (late 2017 into 2018) � ~9-m diameter aperture � Three instrument to be studied:
○ Optical / NIR Coronagraph (B) ○ UV Multi-object Spectrograph (“LUMOS”) ○ Optical / NIR Multi-resolution Spectrograph
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Three Teams Providing Engineering & Design Support
� Integrated Design Center (IDC): � Comprised of the Optical, Instrument, and Mission Design Labs
(ODL, IDL, MDL) � Concurrent engineering environments for rapid development of a broad,
baseline point design
� Study Office Engineering Team � Shadow IDC efforts and provide depth of analysis and additional design
where IDC is unable to � This engineering team ultimately “owns” the final LUVOIR design
� Industry Team (via Cooperative Agreement Notice) � Lockheed Martin, Northrop Grumman, Ball Aerospace, Harris � Leverage expertise & specialized skills to address key elements of the
design study ○ Deployments, I&T, Vibration Isolation, Error Budgeting, Straylight Analysis, etc.
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IDC Study Schedule (2017): � Jan. 17–24 – Telescope Instrument Design Lab (IDL)
� Pre-work 1/10 � Feb. 6–10 – HDI IDL
� Pre-work 1/31 � Mar. 20–24 – Coronagraph IDL
� Pre-work 3/14 � May 15–19 – LUMOS IDL
� Pre-work 5/9 � June 7–13 – Instrument Accommodation IDL
� Pre-work 6/1 � July 10–14 – LUVOIR “A” Mission Design Lab (MDL)
� Pre-work 7/5
� Sept. 11–15 – LUVOIR “B” Optical Telescope Element IDL � Pre-work 9/6
� Oct. 10–16 – LUVOIR “B” Instrument 1 IDL � Pre-work 10/3
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Study Schedule 2017
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3 4 5 6 7 10 11 12 13 14 17 18 19 20 21 24 25 26 27 28 April
31 1 2 3 4 7 8 9 10 11 14 15 16 17 18 21 22 23 24 25 28 29 30 31 1 Aug.
3 4 5 6 7 10 11 12 13 14 17 18 19 20 21 24 25 26 27 28 July Architecture “A” MDL
4 5 6 7 8 11 12 13 14 15 18 19 20 21 22 25 26 27 28 29 Sept. “B” OTE IDL x
1 2 3 4 5 8 9 10 11 12 15 16 17 18 19 22 23 24 25 26 May LUMOS IDL x
29 30 31 1 2 5 6 7 8 9 12 13 14 15 16 19 20 21 22 23 26 27 28 29 30 June Integrated Payload IDL x
27 28 1 2 3 6 7 8 9 10 13 14 15 16 17 20 21 22 23 24 27 28 29 30 31 March Coronagraph IDL x
4 5 6 7 8 11 12 13 14 15 18 19 20 21 22 25 26 27 28 29 Dec.
2 3 4 5 6 9 10 11 12 13 16 17 18 19 20 23 24 25 26 27 Oct. B Instr. 1 x
30 31 1 2 3 6 7 8 9 10 13 14 15 16 17 20 21 22 23 24 Nov. 27 28 29 30 1
2 3 4 5 6 9 10 11 12 13 16 17 18 19 20 23 24 25 26 27 Jan.
30 31 1 2 3 6 7 8 9 10 13 14 15 16 17 20 21 22 23 24 Feb.
“A” OTE IDL x
HDI IDL x
Design Cycle Reports Due x Pre-work Meeting IDC Study Week
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Mechanical Views
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(placeholder sunshield)
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Mechanical Views
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(placeholder sunshield)
(notional instrument bays & backplane support frame)
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Mechanical Views
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(placeholder sunshield and spacecraft)
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Mechanical Views
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Mechanical Views (Deployment)
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Mechanical Views (Deployment)
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Mechanical Views (Deployment)
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Mechanical Views (Deployment)
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Mechanical Views (Deployment)
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Mechanical Views (Deployment)
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Sunshield Sizing
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(dimensions in meters)
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Sunshield Sizing
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Sunshield Sizing
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Sunshield Sizing
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Sunshield Sizing
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Basic Dimensions (meters)
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Basic Dimensions (meters)
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“Yep, it’s big.”
26 Credit: Drew Jones
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LUVOIR “A” OTE Specifications � Instantaneous Field-of-View: 10 arcmin x 8 arcmin � Instantaneous Field-of-Regard: 2π sr, anti-sun � Mirror Coating: Al + LiF + thin protective overcoat of MgF2 or AlF3
� Approx. Reflectivities: ○ 65% @ 105 nm ○ 91% @ 115 nm ○ Average 85% 115 nm – 200 nm ○ Average 88% 200 nm – 850 nm ○ Average 96% 850 nm – 2.5 µm
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0
50
100
100 nm 2.5 µm
835 nm, 85 %
480 nm, 91 %
~97 %
155 nm 80 %
NOTE: This is data for Al+LiF without a protective overcoat.
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LUVOIR “A” OTE Specifications � Instantaneous Field-of-View: 10 arcmin x 8 arcmin � Instantaneous Field-of-Regard: 2π sr, anti-sun � Mirror Coating: Al + LiF + thin protective overcoat of MgF2 or AlF3
� Approx. Reflectivities: ○ 65% @ 105 nm ○ 91% @ 115 nm ○ Average 85% 115 nm – 200 nm ○ Average 88% 200 nm – 850 nm ○ Average 96% 850 nm – 2.5 µm
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0
50
100
100 nm 200 nm
105 nm 65 %
115 nm 91 %
NOTE: This is data for Al+LiF without a protective overcoat.
~80 %
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LUVOIR “A” OTE Specifications � Pointing stability provided by Fine Steering Mirror and
Vibration Isolation and Precision Pointing System (VIPPS): � Repeatability / Step Size: 1 mas � Stability: +/- 0.33 mas during an observation
� Tracking capability provided by VIPPS: � 60 mas / s � JWST is 30 mas / s
� Slew capability provided by spacecraft and gimbal system � Work in progress � Targeting a 90° / 45 min. with a goal of 90° / 30 min. � JWST is 90° / 60 min.
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16:43:03
TMA Telescope GJW 05-Jan-17
3000.00 MM
Primary Mirror (PM)
Secondary Mirror (SM)
Tertiary Mirror (TM)
Fine Steering
Mirror (FSM)
Image Plane (Img)
LUVOIR “A” Telescope Optical Design
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FOV: 10’ x 8’ EFL: ~300 m System F/#: ~20 PM F/#: 1.45 Obscuration: ~3 m
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LUVOIR “A” Telescope Aperture
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15.0 m 12.7 m 3.0 m
� 1.15-m flat-to-flat segments (120x)
� Central ring of array removed to accommodate Aft-optics & Secondary Mirror Obscuration
� Effective area is 135 m2
� Assumes 6 mm gaps
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OTE Focal Plane Allocations
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Field Coordinates on Sky (°)
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Closed-loop Control of PM Segments � Edge sensors:
� Capacitive, inductive, or optical � Provides fast measurements of segment rigid body motions at
picometer level � Baselined for ground-based systems (TMT, GMT, EELT, Keck) � Lab demos show sensitivity at the 10 pm level
� Piezoelectric (PZT) fine-stage in segment actuators � Respond to edge sensor data to move mirror segments � Range of PZT motion is hundreds of picometers; mechanical linkage
reduces that motion to single digit picometers
� Closed-loop system creates a “virtual monolith”
� Technology challenges for LUVOIR � Read-out electronics for high-speed, single digit accuracy � Verify motion reduction with mechanical linkage
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HDI Technical Overview (1/2) � Two-channel Imaging Instrument:
� UV/Vis Imaging (200 nm - ~1.0 µm) ○ Diffraction-limited performance at 500 nm ○ Nyquist sampled at 400 nm
� NIR Imaging (~1.0 µm – 2.5 µm) ○ Diffraction-limited performance at 1.2 µm ○ Nyquist sampled at 1.2 µm
� Each channel will contain a suite of spectral filters:
� Field-of-view: 2 x 3 arcmin � Channel Select Mechanism (CSM) allows:
○ Non-simultaneous observation over each channel’s full band ○ Simultaneous observation in each channel over limited bandpasses or with limited
throughputs
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HDI Technical Overview (2/2) � Exposure times:
� For most extragalactic sources and stellar population observations: ○ Total observation times of up to 200 hrs. ○ Composed of many exposures of 500-1000 s each
� High-speed photometry with 50 ms exposures ○ Limited to small tiles of the focal plane at a time (~150 x 150 pixels)
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HDI Detector Concept – UV/Vis Channel � CMOS Detector
� Pixel size = 5 µm � Nyquist sampled at 400 nm
○ Defined as: 1 pixel = λ / (2*D) ○ λ = 400 nm; D = 15.08 m; ◊ 1 pixel = 2.74 mas
� Read noise: ~2.5 e- � Dark Current: Assume 0.001 e-/pix/s � Operating temperature ~120 K
� Array of 8k x 8k detectors: � Use 5 x 8 tiling of arrays:
○ FOV = 1.90 x 3.12 arcmin ○ 40,960 x 65,536 pixels = 2.68 Gpix ○ 209 x 342 mm focal plane array (including gaps)
� Assume 16 bits/pixel: 5.4 Gbytes per image
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8192 x 8192 Active Region
8192 x 8192 Active Region
8192 x 8192 Active Region
8192 x 8192 Active Region
410 pixel gap (~2 mm)
205 pixel gap (~1 mm)
3 arcmin
2 ar
cmin
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HDI Detector Concept – NIR Channel � H4RG Detector
� Pixel size = 10 µm � Nyquist sampled at 1200 nm
○ Defined as: 1 pixel = λ / (2*D) ○ λ = 1200 nm; D = 15.08 m; ◊ 1 pixel = 8.2 mas
� Read noise: < 5 e- � Dark Current: Assume 0.001 e-/pix/s � Operating temperature ~70 K
� Array of 4k x 4k detectors: � Use 4 x 5 tiling of arrays:
○ FOV = 2.28 x 2.91 arcmin ○ 16,384 x 20,480 pixels = 335 Mpix ○ 167 x 213 mm focal plane array (including gaps)
� Assume 16 bits/pixel: 0.671 Gbytes per image
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4096 x 4096 Active Region
4096 x 4096 Active Region
4096 x 4096 Active Region
4096 x 4096 Active Region
205 pixel gap (~2 mm)
102 pixel gap (~1 mm)
3 arcmin
2 ar
cmin
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HDI Special Modes : � High-Precision Astrometry (for measuring exoplanet mass)
� Astrometric precision of < 5x10–4 pixels � Requires a Pixel Calibration System to calibrate pixel geometry
� Fine-guiding � HDI is the primary fine-guidance sensor for the LUVOIR observatory � Similar to WFIRST operation
○ Requires ability to define regions of focal plane with faster readout ○ Capability shared in both UV/Vis and NIR channels
� Image-based Wavefront Sensing (i.e. phase retrieval) for telescope commissioning and maintenance � Similar to role played by NIRCam on JWST � Elements included in UVIS channel filter wheel assembly:
○ Weak-lenses for generating defocused images ○ Dispersed Hartmann Sensor (DHS) gratings for coarse piston sensing ○ Pupil Imaging Lens (PIL) subsystem
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NIR Channel
NIRM1
NIRM2 NIRM3
NIR FPA
NIR FWA
UVISM1
UVISM3
UVISM2
OTE Focal Plane
POM
Pupil Relay Optics
PRM1
PRM2 UVIS Channel
POM T/T/P-M
FAM FAM
HDI MEB
Cal Laser
UVIS FWA
MB
FiPM UVIS FPA
OTE Avionics
70K
Rad
12
0K R
ad
CSM
FEE
FEE
Cal Source
Optical Bench Thermal Shroud
HDI Memory
HDI Memory
HDI MEB
LL LL
HDI System Block Diagram
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HDI Mechanical Volume in the BSF
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OTE
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NIR Channel
NIR FWA
OTE Focal Plane
FAM
FAM Cal Laser TC
UVIS FPA Sealed
Enclosure
120K Thermal Shroud
TC
70K
Rad
12
0K R
ad
260K
120K
70K 120K
Preamp FE
E
FEE
UVIS Channel
TC
Instrument Enclosure
HDI Memory HDI
Memory HDI
Memory HDI MEB
HDI Thermal Design
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