Lecture 27 10 Imaging Radiometers - University of Arizonaece583/Lecture 27 10_Imaging...and cloud...
Transcript of Lecture 27 10 Imaging Radiometers - University of Arizonaece583/Lecture 27 10_Imaging...and cloud...
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ECE 583Lecture 27
Imaging Visible and Infrared Radiometers
Array Detector ImagersStereo Cloud Hieght & Winds Application
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Why remote sensing -Much of the atmosphere is inaccessible, at least for routine measurements.
From space, only way to provide large enough sample tolarge-scale view of the Earth system
AVHRRSST anomaliesNov 96,97
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Measurement Requirements for Imaging Radiometers
•Spatial resolution (pixel size)
•Number and wavelength of channels
•Spectral width of wavelength channels
•Spatial alignment (registration) between wavelength channels
•Minimum signal measurement accuracy (%)
•Measurement accuracy of radiance (calibration)
Basic Type of Image Scanning Radiometer
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Whiskbroom Imaging
Pushbroom Imaging
Grating Spectrometer Pushbroom Imaging
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Example of MISR Level 2TC data productHurricane Debby
Level 2 Top-of-Atmosphere/Cloud ProductThis contains measurements of cloud heights and winds, cloud texture, top-of-atmosphere albedos and bidirectional reflectance factors, and other related parameters.
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Low Earth Orbit Stereo Imagers
VISIBLEMISR – visible push broom imager, large angle separation
tri-angle wind retrieval
THERMAL INFRAREDATSR – 45o conical scan, 120 sec image separation, ESA
ISIR – 8-12o angle separation, ¼ km resolution, 90 km cross track260 km orbit height, STS-85
ICIR – 10o angle separation, 0.65 km resolution, 1400 km cross track820 km orbit height, Proposed
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Planck’s blackbody function
The nature of Bλ(T) was one of the great findings of the latter part of the 19th century and led to entirely new ways of thinking aboutenergy and matter. Early experimental evidence pointed to two particular characteristics of Bλ(T) which simplify calculations.
Insert fig 3.1
Km.k/hcCmnmW.
cmmW.
mmW.hcC)e(
C)e(
hc
T/C
kT/hc
⋅μ==⋅⋅×=
⋅μ⋅×=
⋅μ⋅×=π=
−πλ=
−πλπ
=
−−
−
−
λλ
λλ
861438710714183231071418323
107141832321
12
2
244
244
24821
51
5
2
2B
B
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Brightness temperature
An important temperature of the physical system, and one differentfrom the thermodynamic temperature in general is the temperaturethat can be attached photons carrying energy at a fixed wavelength. If the energy of such is Iλ, then thistemperature is
Tλ = B-1 (Iλ) = C2/{λln[Iλ λ5 π/C1 +1]}
which is referred to as the brightness temperature
The brightness temperature of microwave radiation isproportional in a simple way tomicrowave radiance:
Rayleigh Jeans Law λT→∞B(T) →kT
The spectral brightnesstemperature of planets and moons
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IR Stereo Imager DevelopmentGlobal Infrared Stereo Observations by LEO UMAD Imaging Radiometer
ISIR Shuttle Hitchhiker ExperimentCOVIR Instrument Incubator Multi Layer Stereo Retrievals
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Application:Diurnal Variation in Cloud Height Distribution
Diurnal variation is a huge factor for cloud distributions.
The best passive retrievals use visible plus IR channels, not possible at night.
IR only CO2 slicing retrievals are limited in resolution.
Active sensors, lidar/radar, now measure nadir only.
Scanning radar/lidar is high cost and limited to a few 100 km’s.
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Velden et al., 2005, Bul. AMS
The impact of satellite-derived polar winds in global forecast models
David A. Santek, CIMSS/Univ. of Wisconsin, Madison, WI
The use of Atmospheric Motion Vectors (AMVs) in Numerical Weather Prediction (NWP) models continues to be an important source of information in data sparse regions. These AMVs are derived from a time-sequence of images from geostationary and polar orbiting satellites. NWP centers have documented positive impact on model forecasts not only in regions where the AMVs are measured, but elsewhere as well. One example is the effect of the Moderate Resolution Imaging Spectroradiometer (MODIS) polar winds on forecasts in the middle and subtropical latitudes. Feature-tracked winds derived from a time-sequence of MODIS satellite imagery over the polar regions are routinely input into many operational global numerical models. These NWP centers report that the winds have a positive impact on forecasts not only in the polar regions, but also into mid- and lower-latitudes, especially in 3 to 5 day forecasts. However, the impact differs for different models. Side-by-side experiments were run, with and without MODIS polar winds, using the National Centers for Environmental Prediction's (NCEP) Global Forecast System (GFS) and the Navy's Operational Global Atmospheric Prediction System (NOGAPS) models. Output from these experiments was analyzed by using a combination of model analyses and forecasts, with sophisticated visualization techniques, to determine the impact to global model fields. The differences in these model fields between the GFS and NOGAPS due to the inclusion of the MODIS winds are explained by data thinning, weighting of the wind observations, and characteristics of their respective assimilation systems.
Goal 1, Low cost IR cloud imagerGoal 2, Stereo Cloud IR in LEOGoal 3, Improved cloud track winds
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Space Shuttle Experiment for Uncooled IR ArraySpace Shuttle Experiment for Uncooled IR ArrayInfrared Spectral Imaging Radiometer (ISIR)Infrared Spectral Imaging Radiometer (ISIR)
Specifications:Specifications:
•• Microbolometer array detector eliminatesMicrobolometer array detector eliminatescooling requirementscooling requirements
•• Push broom imaging eliminatesPush broom imaging eliminatesmechanical scanningmechanical scanning
•• Time delay integration improves NEDTTime delay integration improves NEDTby the square root of the along trackby the square root of the along trackdetector elementsdetector elements
•• 8, 11, 12 & 78, 11, 12 & 7--14 14 μμm channels, 0.1m channels, 0.1--0.010.01ooKKNEDT, 250 m resolution, 82Km swathNEDT, 250 m resolution, 82Km swath
•• Develop Compact, Low Cost and RuggedDevelop Compact, Low Cost and RuggedImaging Infrared Cloud RadiometersImaging Infrared Cloud Radiometers
•• Test the Application of UncooledTest the Application of UncooledMicrobolometer Focal Plane Arrays forMicrobolometer Focal Plane Arrays forSpace Borne Imaging ApplicationsSpace Borne Imaging Applications
•• Observations For Cloud Science: ObtainObservations For Cloud Science: ObtainCombined Passive/Active Remote SensingCombined Passive/Active Remote SensingFrom Joint Shuttle Flight with the SLA LidarFrom Joint Shuttle Flight with the SLA Lidar
Objectives:Objectives:
Microbolometer Array
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Uncooled Microbolometer Array Detector (UMAD) Technology was originally declassified in about 1990.
The ISIR detector was the second pre-production array produced by Loral Space Systems.
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Uncooled Microbolometer FPA
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Altitude ~ 250 km
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ISIR - Time Delay and Integration (TDI)
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IR imaging radiometer showing refractive telescopeand electronics imaging module
Image Signal as a Function of Lens/Telescope F#
Ppix(λ) = I(λ) A Ω Tsys P = Pixel Signal in Watts
A = π D2 /4 D= Lens Diameter
Ω= π (d/L)2 /4 d = Pixel DiameterL = Focal Length
Ppix(λ) = I(λ) (d π / 4F# )2
F# = L/D
Low F# lens gives brightest image-needed for higher noise detectors.
ISIR Lens: F = .73Theoretical Minimum F = .6
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ISIR prior to shuttle Hitchhiker bridgeinstallation
8 mm tape drive
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87 km swath
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Shuttle Roll Maneuvers with ISIR in Video Camera Mode
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ISIR 10.8 um Channel(Coast of New Jersey)
80 km(50 mi)
145 km(90 mi)
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262 K 281 KTemperature (K)
ISIRMultispectral Analysis
Cirrus Particle Size from IR Split Window Brightness Difference
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ISIR on STS-85ZnSe WINDOW
UPPER END PLATE
ADAPTERPLATE
RECORDINGDEVICE
ISIR SENSORASSEMBLY
LOWER ENDPLATE
••Proved Proved uncooleduncooled IR array detectors for spaceIR array detectors for space••First global multispectral IR data set at 1/4 Km resolutionFirst global multispectral IR data set at 1/4 Km resolution••Global cloud science with laser altimeter cloud heightsGlobal cloud science with laser altimeter cloud heights
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Mars Surface Imager BasedOn Microbolometer array detector
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ground track at nadir
1 3
ISIR Trajectory
50 % overlap
Spectral band at moment of image capture
Band 1 = 8.6 um Band 3 = 12.0 um
10.4 degrees FOV
~100 rows at sea level
Height ~ 260 km
~ 79 km 325 columns
~ 48 km 204 rows
Figure 2. Stereo overlap of ISIR image frames acquired at 8.6 and 12 mm roughly 3.5 seconds apart. This gives 50% overlap and complete ground coverage between the two spectral bands
θδ *BHh −=
calculate the height of any feature in the overlapped region from its measured parallax in pixels as:
Stereo Height Retrieval
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Stereo Height Retrieval
Lancaster et al., 2003
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⎪⎪⎭
⎪⎪⎬
⎫
⎪⎪⎩
⎪⎪⎨
⎧
+−
−=Δ
)2
)2
(tan(arctan
1
)2
)2
(tan(arctan
121
θθZB
ZBB
Z
The depth resolution attainable with this method can be expressed in terms of the range-to-baseline ratio and the IFOV. For ratios greater than 30, the depth resolution degenerates to one baseline. The equation below shows the relationship between baseline B; range Z; IFOV, and depth resolution ΔZ/B, for a pixel located at the center of the overlapped region. Simple geometry and trigonometry results in the expression:
This equation can be used to give height uncertainty in km as a function cloud height h, by replacing the range Z with (H - h). The figure shows the results for an altitude of 266 km, a baseline of 25.9 km and 0.903 milliradian IFOV. For a single-pixel cloud at 10 km altitude, the height uncertainty would be +/_ 2.3 km (without using a sub-pixel algorithm to search for the parallax giving the best correlation between views).
0 2 4 6 8 10 1 2 1 4 16 1 8 202 .1
2 .1 5
2 .2
2 .2 5
2 .3
2 .3 5
2 .4
2 .4 5
2 .5
c lo ud a lti tud e in k m
heig
ht u
ncer
tain
ty in
km
IS IR IF O V 0 .903 m rad , a ltitud e 266 km , bas e line 25 .9 km
Depth resolution expressed as ± height uncertainty for clouds ranging between sea level and 20 km. Graph is for ISIR stereo imaging.
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278234Brightness Temperature (K)
256 267245 3500Altitude (m)
1150075005500 9500
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ISIRCloud Heights from Stereo Analysis Compared to Shuttle
Laser Altimeter Cloud Heights
Stereo
Laser
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Issues for Stereo Accuracy
Measurement physics:• Photon penetration / Distributed source function• Multi cloud layers• Cloud top contrast• Cloud motion
Instrument issues• IFOV and stereo view separation• NEDT
Height uncertainties driven by measurement physics
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Figure 4. Composite imagery at 8.6 and 12 um, comprised of two frames in each band. Only the regions of overlap are shown. The motion of the ISIR sensor is from the bottom towards the top of the panels. Figure 5. Brightness temperature histograms of
composite thermal images in Figure 4.
230 240 250 260 270 280 2900
200
400
600
800
10008.6 um Tbr Histogram
Tbr in K
num
ber o
f pix
els
230 240 250 260 270 280 2900
200
400
600
800
100012 um Tbr Histogram
Tbr in K
num
ber o
f pix
els
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8.6 micron ROI masks 12 micron ROI masks
Figure 6. Binary ROI (region-of-interest) masks for the stereo pair in Figure 4 are shown, created by assigning a value of 1 to all pixels at or below the indicated brightness temperature, and 0 to all pixels above that temperature. The highest clouds are in the masks at the top of the frame, and are arranged in order of increasing temperature, and hence decreasing altitude.
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Figure 8. Discrete height maps generated from ROI masks and stereo retrieval. The altitudes are tabulated in the table above.
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Figure 12. 8 um stereo height composite and line plot of stereo heights along nadir column for composite image obtained between 8:17:18:55:31 to 8:17:18:58:04 GMT, or from 90 W, 50 N, to about 60 W, 30 N.
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Stereo Retrieval ResearchMultiple Cloud Level Profile Retrieval
Objective: Identify common cloud layers for stereo height retrieval
Approach: Exploit correlation between infrared TB and cloud height- Define cloud mask based up TB
- Identify parallax shift for cloud mask thru pattern matching- Assign retrieved height to all pixels enclosed by mask
Result: Stereo height retrieval for multiple cloud layers
2
1
33 cloud layers
12 3
Manizade et al., 2005
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Free Flyer Prototype Development Compact Visible and Infrared Radiometer
• ½ km resolution from 600km• four IR channels between 3.5 and 12.5 um• IR detector: Uncooled, microbolometer Focal Plane Array
• Time Delay and Integration to improve S/N• 0.1oK accuracy at 300 K • up to four visible channels between 440 and 860 nm• Visible detector: Uncooled, CCD linear array
• Mass: 20 kg; Power: 35 W
Internal Blackbody
45 cm
Optic Bench
IR DetectorElectronics
Flip mirrorAssembly
VisibleCameraAssembly
IR CameraAssembly
•Separate visible and infrared cameras
•Array detector pushbroom imaging
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COVIR Design Upgrades
Fig. 2 Conceptual drawing of detector assembly
TEC Cooler
DetectorArrayStrip Filters
3.7 μm12 μm10.8 μm10 μm
• Eliminates dead time between filters
- Allows for inclusion of 4th passband with TDI 15
• Eliminates possible mechanical failure of the filter wheel.
- Provides greater reliability
Move from a filter wheel design to using strip filters
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Detector Specifications Infrared
Visible
Type Uncooled microbolometer FPA
Format 327 x 240
Operation Time Delay and Integration
Channels 4
Type CCD linear array
Format 4 rows of 1x1520
Operation Continuous readout
Channels 4
240 pixels
320 pixels
Figure 3 Microbolometer array with strip filters
60 pixels
60 pixels
60 pixels
60 pixels
3.55
-3.9
5 m
icro
n ch
anne
l
11.5
-12.
5 m
icro
n ch
anne
l
10.3
-11.
3 m
icro
n ch
anne
l
8.0
-9.0
mic
ron
chan
nel
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Optics:Calculations and Trade Studies
} 0.125mm
} 0.5mm{0.5mm
Detector 3.5 3.9 μ→
Not to Scale
sapphire Step
{vignetted
region
{
3.4vignetted
region pixels=
{17
vignettedregion pixels=
same
Analysis: Vignetting calculations for filter strips indicate possible TDI frame rates as a function of F/#:
10.3 11.3μ→11.5 12.5μ→
θ
{s′′{s′′
{s′′
{s′′
L
s′
8.5 10.5μ→
Detector
s′s′
Design Support: Design support for the detector sub-assembly: optical path lengths, element spacings, and materials:
TEC Cooler
DetectorArray
A/R Coated Germanium Window
Strip Filters
Filter Substrate 15 mils
3-5 mils
3.7 μm12 μm10.8 μm10 μm
Ghost Images: calculations to determine guidelines for element spacing:
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A triplet lens design solution: Spotsize Goal = 46 μ; Design Result = 35 μEncircled energy = 80%
IR Optical Prescription Data:F/0.8; Focal length = 55.52 mm; Aperture = 69 mm
IR Lens Mount (Janos):
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4 (11um, 12umx2, 3.7 um)Number of channels
46.25 umPixel Size
60 frames/secondFrame Update Rate
PushbroomType of Imaging
Refractive, F/0.9Telescope
320x240 pixelsFormat
Uncooled microbolometer FPADetector
0.1 oKNEDT
Design ParameterProposed IR Camera
Focal plane array showing bandpass filters priorto installing germanium package window
IR imaging radiometer showing refractive telescopeand electronics imaging module
Technology benefits: • No cooling = low power consumption• No cooling = no thermal radiators• Focal plane array = Simultaneous 2D
imaging• Focal plane array = compact, lightweight• Focal plane array = stereo imaging
Compact Visible and Infrared Radiometer
IR Imaging radiometer is built around an uncooled microbolometer array detector (UMAD)
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Compact Infrared and Visible Imaging Radiometer -COVIR
Small Multispectral Infrared and Visible Imaging Radiometer
Cloud and Surface Observations With Combined Spectra and Spatial
Imaging
Follow on to ISIR-01 experiment on STS-85
Instrument Incubator Project - Engineering Model Development
Objective: – Moderate resolution (1/2km) 5 channel
visible and near infrared imaging– Combined spatial and spectral IR imaging– Small size and low cost
6”
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CoVIR IIP InstrumentFlight Breadboard
200 km Swath
Flight Mission Instrument Development
Compact Visible and IR Imaging RadiometerVertical Imaging Cloud Infrared Imager
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Mission Proposal Design StudySIRICE IR Imaging Radiometer
PUSHBROOM SCANNING RADIOMETER
FOV C
amera
1
FOV Camera 2FOV Camera 3
FOV of sub-mm conicalScanner
Cro
ss-tr
ack
dire
ctio
nGround-track of sub-mm conicalscanner
1400 km
3 IR spectral channels
• IR camera stares nadir or at an angle (fore or aft)
• Image is sampled sequentially in each of the 3 spectral channels
• Time Delay and Integration is used to achieve NEDT < 100 mK
• Image spatial resolution ~ 1.5 km/pixel
• Two (possibly three) cameras needed to cover 90o FOV
TECHNICAL CHALLENGES:• Calibration of the multiple cameras
• Use of TDI requires spacecraft attitude be controlled to align image motion with 1 dimension of detector array
PRACTICAL BENEFITS:• Natural mode of operation for 2D array
• GSFC has developed two of these systems already
• Most of the technical challenges have been worked out
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IRCIR Development
• Three or four cameras based on COVIR design
• Each camera covers a 30 degree swath with a max 22.5 fore-aft angle for stereo
• Basic 1 km resolution with onboard compression and possible stereo processing
• GSFC PI and management
• Cost competition build options:- University and GSFC partnership - GSFC in house- Contracted to industry
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IRCIR Characteristics – Signal to Noise Ratio
SIRICE Requirements:• 1 um passband filters• Three channels 11 um, 12um, 7 um• NEDT < 100 mK
COVIR Spectral Channels
0
10
20
30
40
50
60
70
80
90
100
3000
3184
3368
3552
3736
3920
4104
4288
4472
4656
4840
9046
9414
9782
1015
0
1051
8
1088
6
1125
4
1162
2
1199
0
1235
8
1272
6
1309
4
1346
2
Wavelength (nm)
Tran
smis
sion
(Per
cent
)
NEDT ~ (200/Δλ)(F/#)2 mK•μmFor λ~11 um, 300K scene, F/1
Current UMAD technology:
SIRICE Results:
243 mK
350 mK
190 mK
NEDT (mK)(No Averaging)
<100 mK
<100 mK
<100 mK
NEDT (mK)(w/ Averaging)
12
7
11
Wavelength (um)
• Need 3x improvement in SNR
• Include 10 pixels in TDI average (√10 ~ 3)
• Resample single pixel 2x in 0.3 s scan time at 60 fps with <1/10 pixel registration error(SNR increases by √2 ~1.4)
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1.5 2.0 2.5 3.0 3.5 4.54.0Resolution (km)
45 deg
TDI
Camera 1 Camera 2
Camera 3 Camera 4
• Mirrors rotate ~45 deg off-nadir to view cloudscene
• Mirrors rotate ~270 off-nadir to view blackbodycalibration source
• Mirrors rotate ~80 off-nadir to view space forcalibration measurement
Camera 1
Camera 2
Camera 3
Camera 4
IRCIR Global LOE Cloud Imager
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Front View
Camera Heads
Electronics box
4 Calibrationblackbodies
Servo-motor,capstan drive combo
4 rotating mirrors
Camera Heads
18.3 cm
14.1 cm
14.4 cm
17.3 cm
18.4
cm
24.3 cm
Infrared Cloud Imaging RadiometerVIRCIR Concept
1400 km Swath Cloud Retrieval
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IRCIR Instrument Concept for Stereo Cloud Track Winds
Science• IR Cloud Information• Stereo Cloud Height• Winds (flying in orbit with NPP)
IRCIR Provides Full Cross-track Coverage using Four 640 x 480 pixel Uncooled Silicon Micro-bolometer Arrays
4 Imaging ArraysWith associatedLens assemblies
RotatableScene Mirror
Protective DrumBaffle (rotates withScene Mirror)
Cross-trackFields of View
OpticsBench
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IRCIR Located on Dedicated Deck Behind SM4
This view of the instrument isrotated about the S/C axis by 90°
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81.28cm
101.6cm
75cm
• Meets all present GOES Imager Requirements– Imaging Radiometric
Performance– Envelope– Mass, Power
• Development Schedule– 27 months to flight unit
delivery– Integration of modern
(available) hi-reliability components
Advanced Technology GOES Imager
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66
Rapid Response IR/Visible GOES Meteorological Imager
Instrument Characteristics• 5 band Step-Staring Imager
– IFOV: 4 km (IR) /1 km (vis)– FOV: 1000 km x 960 km (Present
320x240 LW FPA)– Field of Regard: +/- 20 deg.– 4-band IR radiometer (~ 7, 11,12, 13.5
μm with uncooled IR FPAs , 3.9 μm with high temperature(190K) HCT FPA)
– 1-band visible (CCD)• Favorable Accomodation Parameters
– <90 kg/ 0.4 m3/ 100 W, and no cryoradiators!
Technology and Programmatic Readiness • Technology for all instrument components is sufficiently mature (NASA TRL 7 or higher)..• Preliminary investigation of instrument/spacecraft interface shows no notable concerns.• Schedule, while aggressive, is consistent with other programs of similar complexity.
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NESR for 10.8 μm Channel (Standard LW Window)
• Detector NEP: 3.5 pW/(Hz)1/2
• System Transmission: 50%• Detector Area: 46x46 μm• Solid Angle: (f/1.4)• Noise Bandwidth: 7.5 Hz (4)• Modulation Frequency: 10 Hz• Incoherent Sample Summing
Improvement Factor: (20)1/2
• Spectral Pass Band: 88 cm-1
28 Micron Square Uncooled Bolometer NEP
1.00E-14
1.00E-13
1.00E-12
1.00E-11
1.00E-10
0.1 1 10 100 1000 10000 100000Frequency(Hz)
NEP
(W/rt
Hz)
NEP_Thermal
NEP_johnson
NEP_1/f pix
Predicted NESR: <0.07 mW/str/m2/cm-1
Required NESR: 0.272 mW/str/m2/cm-1 (200 mK NEDT @ 300K)
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JEM Attached Payload Modules