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Spacecraft

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100 100% of sky visible at least 80 51 continuous days

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Continuous Days Available per year

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Sun

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10-5 Mission Requirements 200 MJy/sr

-1 10-6 m 3.9 MJy/sr μ -1

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Minimum Zodiacal 10-8 Background Watts m Watts

10-9 0 5 10 15 20 25 30

Wavelength (μm)

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Folding secondary Glare Stop Aft mirror Optical support Subsystem strut Primary (Tertiary Mirror mirror & Segment fine steering (1 of 18) mirror)

Deployment

Primary Mirror Backplane Motor

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OTE ISIM V3 (anti-spacecraft)

(V1, V3)

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Primary f/#: 20.0 Mirror Effective : 131.4 m

PM diameter = 6.6 m (circumscribed circle)

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1.15 Region in which RMS WFE <131nm NIRCam NIRSpec

MIRI

+3.4 Vertical Field Position (arcmin in +V3 Axis) -9.1 0 9.1

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flat to flat

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Actuator development unit Lightweighted Actuator for radius Beryllium Mirror

of curvature adjustment

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First Initial Capture Final Condition NIRCam After Step 1 18 individual 1.6-m diameter aberrated PM segments: 1. sub-telescope images <100µm, Segment PM segments: < 1 mm, < 2 arcmin tilt < 2 arcsec tilt Image SM: < 3 mm, Capture SM: < 3 mm, < 5 arcmin tilt <5arcmintilt After Step 2 Primary Mirror segments: 2. Coarse Alignment < 1 mm, < 10 arcsec tilt WFE < 200 µm (rms) Secondary mirror aligned Secondary Mirror : Primary RoC adjusted <3mm,<5arcmintilt After Step 3 3. Coarse Phasing -Fine WFE: < 250 µm rms WFE < 1 µm (rms) Guiding (PMSA piston)

After Step 4 4. Fine Phasing WFE: < 5 µm (rms) WFE < 110 nm (rms)

After Step 5 5. Image-Based WFE: < 150 nm (rms) WFE < 110 nm (rms)

Wavefront Monitoring

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Fixed Solar Arrays (1 of 2) High Gain Antenna (Ka Band and S Band) 1lb Dual Thruster Modules (1 of 4)

Deployable Radiator Stationkeeping Shade Thruster

Fine Sun Sensors Trackers (3)

Radiator Surface Coarse Sun Sensors 5lb Dual

(2 of 4) Thruster Modules (1 of 2)

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Filter Wheels

Long Wavelength Short Detectors Wavelength Pick-off Detectors

Mirror

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NIRCam Collimator Camera Pickoff Mirror Optics

Telescope Pupil Filter Focal Wheel Wheel Surface Coronagraph Wedge Not to scale

Coronagraph Not to scale Image Masks Calibration Source FPA NIRCam FPA Optics Field-of-View

Without Coronagraph Wedge With Coronagraph Wedge

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Fixed Slits and IFU

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Detector Array 3.6’ (2 x 2048 x 2048 pixels)

Direction of Dispersion

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MIRI Allocation 4QPM 15.5µm, 26”x26” Imager FOV 4QPM 11.4µm, 26”x26” Imaging 0.11”/pixel, 2.39 arcmin2 4QPM 10.65µm, 26” x 26”

Lyot Mask LRS 23μm, 30” x 30” 5.5” x 1”

Medium Resolution

Spectrometer FOV

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Channel 2 (7.4 - 11.8 μm)

Channel 3 (11.4 - 18.2 μm)

Channel 4 (17.5 - 28.8 μm) Wavelength/Velocity

IFU Output Format

Spectrometer input “slit”

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1 week (L + 6 months) Commissioning Complete interval (L + 113 da ys) Initiate Observatory Commissioning

(L+ 41 min) (L + 4 days) Solar Array OTE (L + 28 da ys) Initial Deployment Deployment WFS&C Commissioning (T0) Launch (L + 63 da ys) Cool (L + 2 days) down ne ar ste ady (L + 14 hr) High state; Repeat hield Stowed Observatory Gain Antenna Deployment WFS&C

Deployment Commissioning in 5meter shroud

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support structure

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