Kazuhiro TANAKA GCOM project team/JAXA April, …May 2016 June 2016 July 2016 Initial Geometry Test...

Kazuhiro TANAKAGCOM project team/JAXA

April, 2016

@ SPIE Asia-Pacific 2016 at New Dehli, India 1http://suzaku.eorc.jaxa.jp/GCOM_C/index_j.html

GCOM mission and satellites SGLI specification and IRS overview Current Status IRS Proto Flight Test ◦ Verification Flow◦ Verification Matrix

Early Test Results◦ Geometric Performance Test◦ Radiometric Performance Test for Shortwave Infrared

Channels◦ Radiometric Peformance Test for Thermal Infrared Channels◦ Spectral Response

Conclusion

SPIE Asia-Pacfic 2016, New Dehli, India 2


Global observation satellite system as JAXA’s GEOSS contribution. 2 satellite series for 5 years, total 13 years observation.GCOM-W Microwave radiometric observation for WATER CYCLE

using AMSR2 (AMSR-E follow on)GCOM-C Optical multi-channel observation for RADIATION

BUDGET and CARBON CYCLE using SGLI (GLI follow on)

GCOM-Cis scheduled for launchin 2017.

GCOM-C(CLIMATE)

SensorAdvanced Microwave Radiometer 2 (AMSR2)

Passive Microwave ObservationWater vapor, soil moisture etc

SensorSecond Generation Global Imager(SGLI)

Optical Observation 380nm – 12 micronCloud, Aerosol, Vegetation, Chrolophl etc

GCOM-W(WATER) AMSR2

SGLIGCOM-W “SHIZUKU” was launched on May 18,2012.


Second generation Global Imager (SGLI)on GCOM-C satellite

SGLI IRSELU

+ X

flight direction

+Y

+ Z earth

deepspace

SGLI VNRELU

SGLI IRSSRU

SGLI VNRSRU

SGLI Second Generation Global ImagerVNR Visible and Near Infrared RadiometerIRS Infrared Scanning RadiometerSRU Scanning Radiometer UnitELU Electronic Unit

Mission Life > 5 years

Solar Paddle > 4000w （End of Life）

Mass about 2,000kg

SGLI channels

CH

λ Δλ Lstd Lmax NP,PL,SWI: SNR at LstdTIR: NEΔTat 300K

IFOV

NP, PL, SWI: nmTIR: μm

NP, PL, SWI: W/m2/sr/μmTIR: Kelvin

m

VN1 380 10 60 210 250 250VN2 412 10 75 250 400 250VN3 443 10 64 400 300 250VN4 490 10 53 120 400 250VN5 530 20 41 350 250 250VN6 565 20 33 90 400 250VN7 673.5 20 23 62 400 250VN8 673.5 20 25 210 250 250VN9 763 12 40 350 1200 250/1000VN10 868.5 20 8 30 400 250VN11 868.5 20 30 300 200 250PL1 673.5 20 25 250 250 1000PL2 868.5 20 30 300 250 1000SW1 1050 20 57 248 500 1000SW2 1380 20 8 103 150 1000SW3 1630 200 3 50 57 250/1000SW4 2210 50 1.9 20 211 1000T1 10.8 0.7 300 340 0.2 250/1000T2 12.0 0.7 300 340 0.2 250/1000

GCOM-C SGLI characteristics

OrbitSun-synchronous(descending local time: 10:30)Altitude 798km, Inclination 98.6deg

Mission Life 5 years (3 satellites; total 13 years)

Scan Push-broom electric scan (VNR)Wisk-broom mechanical scan (IRS)

Scan width 1150km cross track (VNR: NP & PL)1400km cross track (IRS: SWI & TIR)

Digitalization 12bitsPolarization 3 polarization angles for PLAlong track direction

Nadir for NP, SWI and TIR, +45 deg and -45 deg for PL

On-board calibration

VN: Solar diffuser, LED, Lunar calmaneuvers, and dark current by masked pixels and nighttime obs.

SWI: Solar diffuser, LED, Lunar, and dark current by deep space window

TIR: Black body and back ground by deep space window


SGLI Specification• The SGLI features are 250m spatial resolution (VNR-NP, SW3 & TIR) and

polarization/along-track slant view channels (VNR-PL), which will improve land, coastal, and aerosol observations.

Multi-angle obs. for 674nm and 869nm

250m over the Land or coastal area, and 1km over offshore


Earth

Flightdirection

Infrared Scanning Radiometer(SGLI-IRS)

OBS Light

SCANMOTOR

BLACKBODY

TIR-DET

SterlingCooler

OpticalBench

SWI-DET

Engineering model of SGLI-IRSfor vibration test configuration1.4m

0.6m

Weight:193kgPower: 400W


Current Status SGLI consists of two sensors, SGLI-VNR and

SGLI-IRS IRS sensor system manufacturing and

integration were finished. The sensor level pre-flight tests started in

December 2014. IRS test is in the final stage before the delivery

to the satellite system. Satellite level test will start within 2016 and

planned for launch in 2017.


March 17, 2016 at TSKUBACompatibility test with satellite system

SGLIVNR

SGLIIRS

Flightdirection


Colimeter

IRS-SRU

Rotation Stage

IRS-SRUIntegrationSphere

IRS-SRU

TempControledBlackBody

SpaceBlackBody

Dynamic Range / Background Detector Uniformity

NEdT Detector Temperature

Linearity BlackBody

Dynamic Range Detector UniformitySNR Stability (Dark, Signal)Linearity Onboard Calibrator (Halogen, LED)

BlackBody

FOV, IFOV Alignment Scanning PerfomanceMTF Registration

May 2016 June 2016 July 2016

InitialGeometry Test

InitialIntegrating Sphere

Solar DirectionDependence

ELU-SRU I/FTest

Thermal VacuumTest

Satellite I/F TestEMC Test

VibrationAcoustic Excitation

Dec. 2014 March 2015 April 2015 August 2015 November 2015 March 2016

FinalIntegrating Sphere

FinalGeometry Test

TIR Radiometry

ComparisonInitial SWI Radiometry Final SWI Radiometry

Environment Test Campaign

ComparisonInitial TIR Health Check Final TIR Health Check

ComparisonInitial IRS Geometry Final IRS Geometry

SWI Radiometry TIR Radiometry IRS Geometry

NOW▽


Component Test& Integration

Initial ElectricPerformanceTest (I-EPT)

Thermal VaccumTest (TVT)

EMC TestVibration

Acoustice Excitation

Final ElectricPerformanceTest (F-EPT)

GeometryFOV, IFOV Component Rotation Table - - - Rotation TableMTF Component Rotation Table - - - Rotation TableAlignment Integration Rotation Table Cube Mirror - Cube Mirror Rotation TableScanning Perfomance Component Rotation Table Resolver Resolver Resolver Rotation TableRegistration Component Rotation Table - - - Rotation Table

SWI RadiometryDynamic Range Component Integrating Sphere - - - Integrating SphereSNR Component Integrating Sphere - - - Integrating SphereLinearity Component Integrating Sphere - - - Integrating SphereDetector Uniformity Component Integrating Sphere - - - Integrating SphereStability (Dark, Signal) Component Integrating Sphere - - - Integrating SphereOnboard Calibrator (Halogen) Component Calibrator Test Calibrator Test Calibrator Test Calibrator Test Calibrator TestOnboard Calibrator (LED) Component Calibrator Test Calibrator Test Calibrator Test Calibrator Test Calibrator TestOnboard Calibrator (Light Guide) Component Angle Dependence - - - -

TIR RadiometryDynamic Range / Background Component - TVT Test - - -NEdT Component Black Body TVT Test Black Body Black Body Black BodyLinearity Component - TVT Test - - -Detector Uniformity Component Black Body TVT Test Black Body Black Body Black BodyDetector Temperature Component Ambient Test TVT Test Ambient Test Ambient Test Ambient TestBlackBody (On-Board) Component Ambient Test TVT Test Ambient Test Ambient Test Ambient TestBlackBody (Ambient) Component Ambient BBC / LN2 - Ambient BBC Ambient BBC Ambient BBCBlackBody (TVT) - - TVT Test - - -

Objectives◦ to confirm that IRS was integrated mechanically as designed◦ to obtain the geometry data processing parameters after the launch

detector position and alignment is measured◦ rotation stage (3 rotation axis, 2 linear translation)◦ collimator (halogen lamp for shortwave IR, black body for thermal IR)

Test results :◦ MTF > 0.35 req.◦ detector position < 0.2 pixel (250m) accuracy


-15

-10

-5

0

5

10

15

-15 -10 -5 0 5 10 15

ATPi

xel[

250m

]

CT Pixel [250m]

TIR-1 req

TIR-2 req

TIR-1 meas.

TIR-2 meas.

SWI-2 req

SWI-4 req

SWI-2 meas

SWI-4 meas.

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

-1 -0.5 0 0.5 1

MTF

[@N

yqui

st F

req.

]

Defocus Position [mm]

MTF Defocus Curve (IRS SWIR)SW2 AT

SW2 CT

SW4 AT

SW4 CT

MTF spec.=0.35


Objectives◦ to confirm that IRS/SWI was integrated radiometrically as designed◦ to obtain the gain parameter for the data processing

Traceable to the Japanese national standard◦ Gold coated integrated sphere developed by JAXA’s sensor group◦ Calibrated with fixed point black body

Test results :◦ all requirements met.◦ Small offset non-linearity in high temperature ; under study◦ The humidity effects in 1.36micron channels ; under study.

Saturation

Radiance Corrected Radiance Corrected (4095DN) Lstd Worst Lmax Lstd Dark Lstd[micron] [nm] [W*] [DN] [W*] [DN] [DN] [W*] [W*/DN] [%] [DN] [DN] [DN] [DN] (min)

1.05 21.8 253.3 3529.0 58.2 811.5 102.1 282.3 0.0707 0.2% 5.1 1.5 0.9 0.8 942 500

1.38 20.7 102.4 3385.4 8.3 270.3 99.8 118.6 0.0297 -0.9% -8.6 4.1 0.8 0.8 329 150

SWI-3 1.63 191.3 49.8 3723.6 3.0 220.0 93.2 50.5 0.0127 -1.1% -7.7 3.8 2.2 2.0 100 57

SWI-4 2.21 51.9 20.0 3668.5 1.9 342.8 97.0 21.4 0.0054 -0.1% 3.3 2.2 0.9 0.9 368 211[W*] = [W/m2/str/µm]

SNRNoise

SWI-2

BandWidth

Spec.

Lmax Lstd Linearity Error (max)Gain(min)Dark

Signal Level (min)λcCh

SWI-1

GainSigma (max)


-20

-15

-10

-5

0

5

10

15

20

0 50 100 150 200 250

Line

arity

Erro

r[D

N]

[W/m^w/str/micron]

SWI-1 : 1.05micron

req. [DN] Pixel-1 Pixel-2

Pixel-3 Pixel-4 Pixel-5

-3.0%-2.5%-2.0%-1.5%-1.0%-0.5%0.0%0.5%1.0%1.5%2.0%2.5%3.0%

0 50 100 150 200 250

Line

arity

Erro

r[%

]

[W/m^w/str/micron]

SWI-1

req. [%] Pixel-1 Pixel-2


-20

-15

-10

-5

0

5

10

15

20

0 50 100

Line

arity

Erro

r[D

N]

[W/m^w/str/micron]

SWI-2 : 1.39micron



-3.0%-2.5%-2.0%-1.5%-1.0%-0.5%0.0%0.5%1.0%1.5%2.0%2.5%3.0%

0 50 100

Line

arity

Erro

r[%

]

[W/m^w/str/micron]

SWI-2



-20

-15

-10

-5

0

5

10

15

20

0 10 20 30 40 50 60

Line

arity

Erro

r[D

N]

[W/m^w/str/micron]

SWI-3 : 1.63micron



-3.0%-2.5%-2.0%-1.5%-1.0%-0.5%0.0%0.5%1.0%1.5%2.0%2.5%3.0%

0 10 20 30 40 50 60

Line

arity

Erro

r[%

]

[W/m^w/str/micron]

SWI-3



-20

-15

-10

-5

0

5

10

15

20

0 5 10 15 20

Line

arity

Erro

r[D

N]

[W/m^w/str/micron]

SWI-4 : 2.21micron



-3.0%-2.5%-2.0%-1.5%-1.0%-0.5%0.0%0.5%1.0%1.5%2.0%2.5%3.0%

0 5 10 15 20

Line

arity

Erro

r[%

]

[W/m^w/str/micron]

SWI-4



a. 1.6μm LED with temperature correction for the absolute referenceb. Halogen color temperature and emissivity estimation from the lab. datac. Relative and absolute calibration for all 4 channelsd. Total calibration error is estimated as 1.6 to 4.3 % (1σ;preliminary)


17

18

19

20

21

22

23

24

5 10 15 20 25 30 35

[μW

]

degree C

LED TempDependence

2200

2250

2300

2350

2400

2450

2500

2550

2600

7 8 9 10 11 12 13

Colo

rTem

p[K

]

Lamp Volt [V]0

0.2

0.4

0.6

0.8

1

1.2

0 500 1000 1500 2000 2500 3000

Norm

alize

d Rad

ianc

e

Wave length [nm]

Color temperature2200230024002500260027002800290030003100Lamp Data

b. b.

b. a.


Objectives◦ to confirm that IRS/TIR was integrated radiometrically as designed.◦ to obtain the gain parameter

Specially designed black body for thethermal vacuum environment

Test results :under calculation

SaturationRadiance Corrected Radiance Corrected (4095DN) (max) Tstd Worst Tmax Tstd Space Tstd

[K] [DN] [K] [DN] [340K] [DN] [K/DN] [%] [%] [DN] [DN] [DN] (max)2150.0 1263.4 158% 534.9 0.0528 0.35% 1.89% 1.3 1.2 1.1 0.06 0.2

2146.0 1257.7 138% 986.8 0.0529 0.35% -0.88% 1.4 1.3 1.3 0.07 0.2

2071.9 1261.0 159% 676.3 0.0579 -0.44% -1.99% 1.6 1.5 1.5 0.09 0.2

2056.1 1260.5 133% 1225.1 0.0579 -0.80% -1.97% 1.8 1.8 1.7 0.10 0.2250m resolution, TDI = YES, Upper = BOL(COLD) / Lower = EOL(HOT)

10.78 0.74

TIR-2 11.97 0.77

TIR-1

Ch λcBandWidth

Gain

[micron]

Signal Level (min) BackGroundTmax Tstd Gain

300KError (worst)

340

340

300

300

NoiseSigma (max) NEdT [K]

Spec.(500m)

σtemp < 0.1KTempStability < 0.01K

εwitness > 0.97


-15

-10

-5

0

5

10

15

170K 220K 270K 320K

Line

arity

Erro

r[DN

]

TIR-1 10.8μm Linearity Error [DN]

On-Board BBC

-3%

-2%

-1%

0%

1%

2%

3%

170K 220K 270K 320K

Line

arity

Erro

r[%

]

TIR-1 10.8μm Linearity Error [%]

Pix1 Pix2 Pix3 Pix4 Pix5Pix6 Pix7 Pix8 Pix9 Pix10Pix11 Pix12 Pix13 Pix14 Pix15Pix16 Pix17 Pix18 Pix19 Pix20On-Board BBC

-15

-10

-5

0

5

10

15

170K 220K 270K 320K

Line

arity

Erro

r[DN

]

TIR-2 12.0μm Linearity Error [DN]

-3%

-2%

-1%

0%

1%

2%

3%

170K 220K 270K 320K

Line

arity

Erro

r[%

]

TIR-2 12.0μm Linearity Error [%]

Pix1 Pix2 Pix3 Pix4 Pix5Pix6 Pix7 Pix8 Pix9 Pix10Pix11 Pix12 Pix13 Pix14 Pix15Pix16 Pix17 Pix18 Pix19 Pix20On-Board BBC


LowerWavelength

UpperWavelength

LowerWavelength

UpperWavelength

SWI-1 1,054.93 1,044.40 1,065.45 21.05 1,054.86 1,043.90 1,065.69 21.78

SWI-2 1,385.31 1,375.25 1,395.37 20.12 1,385.34 1,375.01 1,395.66 20.65

SWI-3 1,633.70 1,536.20 1,731.20 195.00 1,634.65 1,539.36 1,730.62 191.26

SWI-4 2,210.62 2,185.43 2,235.81 50.38 2,210.91 2,184.73 2,236.59 51.86

TIR-1 10,782.67 10,414.98 11,150.35 735.37 10,787.18 10,420.94 11,156.63 735.69

TIR-2 11,974.75 11,581.97 12,367.53 785.56 11,952.36 11,557.59 12,327.17 769.58

Half ResponseBand width

FWHM Spectral Response [nm] Weighted Spectral Response [nm]Half ResponseCenter

Wavelength Band widthCenter

Wavelength

0

100

200

300

400

500

950 1000 1050 1100 1150

Tota

l R

esp

ons

e[m

A/W

]

[nm]

SW1

0

100

200

300

400

500

600

700

800

1300 1350 1400 1450 1500

Tota

l R

esp

onse

[mA

/W

]

[nm]

SW2

0

100

200

300

400

500

600

700

800

900

1450 1500 1550 1600 1650 1700 1750 1800

Tota

l R

esp

onse

[m

A/W

]

[nm]

SW3

0

100

200

300

400

500

600

700

800

900

1000

1100

2100 2150 2200 2250 2300 2350Tota

l R

espo

nse

[m

A/W

][nm]

SW4

0

0.2

0.4

0.6

0.8

1

1.2

9500 10000 10500 11000 11500 12000

Norm

aliz

ed

spectr

al r

esp

ons

e

[nm]

TIR-1

0

0.2

0.4

0.6

0.8

1

1.2

10500 11000 11500 12000 12500 13000

Norm

aliz

ed

spectr

al r

esp

onse

[nm]

TIR-2

SGLI consists of two sensors, SGLI-VNR andSGLI-IRS

IRS sensor system manufacturing andintegration were finished.

The sensor level pre-flight tests started inDecember 2014.

IRS test is in the final stage before thedelivery to the satellite system.

Satellite level test will start in 2016 andplanned for launch in 2017.


Kazuhiro TANAKA GCOM project team/JAXA April, …May 2016 June 2016 July 2016 Initial Geometry Test...

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Transcript of Kazuhiro TANAKA GCOM project team/JAXA April, …May 2016 June 2016 July 2016 Initial Geometry Test...