1First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
First year on-orbit
calibration
activities of SGLI
on GCOM-C
satellite
Kazuhiro TANAKA
GCOM project team
JAXA
SGLI-VNR image 2018-01-01 20:44 UTC
Topics GCOM and SGLI
SGLI specification and performance
Initial on-orbit check out results
Thermal band (TIR) performance
Lunar calibration
Next step
2
GCOM-C LaunchH-IIA rocket F-37
01:26:22 UTCOn Dec. 23, 2017
Japanese name“SHIKISAI”
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
3
Global Change Observation Missionfor Climate(GCOM-C)
Global Change Observation Mission for Climate (GCOM-C) carries the opticalradiometer, Second-generation Global Imager (SGLI). SGLI has been designedto provide continuous global observation of the Earth’s surface, ocean, andatmosphere and to understand the global mechanism of carbon cycle andradiation budget. SGLI on GCOM-C consists of two sensor units, VNR (Visibleand Near Infrared Radiometer) and IRS (Infrared Scanning Radiometer).
+X satellitevelocity
+Z Earth
+Y
Second generation
Global Imager
(SGLI)
Visible and Near
infrared Radiometer
(SGLI-VNR)
Infrared Scanning
Radiometer
(SGLI-IRS)
Star
Tracker
Sensor Second generation Global Imager
Orbit
Sun synchronous quasi recurrent
orbit
Altitude : 798km
Inclination : 98.6deg
Local time: 10:30±15min
descending
Size 4.7m(X) × 16.5m(Y) × 2.6m(Z)
Weight 2000kg
Power > 4000W(EOL)
Launch December 23, 2018
Deigned
Life> 5 years
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
4
March 17, 2016 at TSKUBACompatibility test with satellite system
SGLI
VNR
SGLI
IRS
Flight
direction
4.6m (X)
2.2m (Z)
16m (Y)
Satellite 2 ton
SGLI 520kg
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
Second Generation GlobalImager (SGLI)
5
PL telescopes(55deg FOVx 2)
NP telescopes(24deg FOV x 3)
SolarDiffuser
1.5m1.4m
Infrared Scanning Radiometer(IRS)
SunCalWindow
Earth Obs.Window
DeepSpaceWindow
1.5m
0.7m
センサ 概要
SGLI VNR Non-Polarized Obs. (NP) x 11ch, IFOV = 250m, Obs. Swath = 1150km
Polarized Obs. (PL) x 2ch, IFOV 1km, Obs. Swath = 1150km
SGLI IRS Short wave infrared (SWI) x 4ch, IFOV = 250m/1km, Obs. Swath = 1400km
Thermal infrared (TIR) x 2ch, IFOV = 250m, Obs. Swath = 1400km
Visible and Near Infrared Radiometer(VNR)
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
6
Observation wavelength
•19 channels observation
29 standard products
Concentrates on cloud, aerosol and vegetation parameter retrievals
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
7
250m resolution Chl-a Kuroshio currentFeb. 27, 2018
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
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250m resolution SST Kuroshio currentFeb. 27, 2018
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
9
VNR Performancepre-launch test results
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
See details at SGLI Sensor Characterization homepage, http://suzaku.eorc.jaxa.jp/GCOM_C/data/prelaunch/index.html
Pre-Launch Test Performance of VNR (Non Polarized bands, NP)
Saturation Det. Depend.
Radiance Corrected Radiance Corrected (4095DN) Worst Lstd x 0.3 Error (max) Dark Lstd
[micron] [nm] [m] [W*] [DN] [W*] [DN] [DN] [W*] [W*/DN] [%] [DN] [%] [DN] (min)
VN01 380.0 10.7 250m 210 3194 60 913 304 249 0.0657 0.92% 8.4 0.31% 1.37 659 250
VN02 412.5 10.4 250m 250 2910 75 873 263 329 0.0859 1.57% 13.7 0.46% 1.08 786 400
VN03 443.2 10.2 250m 400 3196 64 511 228 484 0.1252 0.75% 3.8 0.43% 1.01 487 300
VN04 489.9 10.4 250m 120 2934 53 1296 307 155 0.0409 0.59% 7.6 0.26% 1.50 858 400
VN05 529.6 19.7 250m 350 3553 41 416 244 379 0.0985 1.19% 5.0 0.65% 0.90 457 250
VN06 566.2 20.0 250m 90 3332 33 1222 330 102 0.0270 1.28% 15.6 0.56% 1.18 1017 400
VN07 672.0 22.3 250m 62 3226 23 1197 270 74 0.0192 1.43% 17.1 0.37% 1.18 988 400
VN08 672.1 22.1 250m 210 3645 25 434 268 220 0.0576 1.88% 8.2 0.50% 0.79 537 250
VN09 763.1 11.4 (250m) 350 3633 40 415 253 370 0.0963 1.87% 7.8 0.51% 0.26 1592
VN10 866.8 21.1 250m 30 2852 8 760 364 39 0.0105 0.30% 2.3 0.36% 1.59 470 400
VN11 867.1 21.3 250m 300 3620 30 362 233 320 0.0829 1.79% 6.5 0.61% 0.74 478 200
Note: SNR of VN09 is specified for 1km Mode. [W*] = [W/m2/str/µm]
Pre-Launch Test Performance of VNR (Polarized bands, PL)
Saturation Det. Depend.
Radiance Corrected Radiance Corrected (4095DN) Worst Lstd x 0.3 Error (max) Dark Lstd
[micron] [nm] [m] [W*] [DN] [W*] [DN] [DN] [W*] [W*/DN] [%] [DN] [%] [DN] (min)
PL01 671.9 20.9 1km 250 2940 25 294 310 322 0.0850 1.51% 4.4 0.83% 0.49 614 250
PL02 866.2 20.3 1km 300 2701 30 270 247 427 0.1111 0.90% 2.4 0.93% 0.42 646 250
[W*] = [W/m2/str/µm]
Sigma (max) SNR
Spec.
Chλc Band Width
Signal Level (min) Noise
Lmax Lstd Dark
(max)
Gain
(min)
IFOV
Gain
Chλc Band Width
Signal Level (min)
Linearity Error (max)
IFOV
Noise
Lmax Lstd Dark
(max)
Gain
(min)
Linearity Error (max) Sigma (max) SNR
Spec.
Gain
(1200)
10
IRS Performancepre-launch test results
Pre-Launch Test Performance of IRS (SWIR bands)
Saturation
Radiance Corrected Radiance Corrected (4095DN) Lstd Worst Lmax Lstd Dark Lstd
[micron] [nm] [m] [W*] [DN] [W*] [DN] [DN] [W*] [W*/DN] [%] [DN] [DN] [DN] [DN] (min)
1.05 21.8 1km 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 1km 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 250m 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 1km 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]
Pre-Launch Test Performance of IRS (TIR bands)
Saturation
Radiance Corrected Radiance Corrected (4095DN) (max) Tstd Worst Tmax Tstd Space Tstd
[m] [K] [DN] [K] [DN] [340K] [DN] [DN/K] [%] [%] [DN] [DN] [DN] (max)
2150.0 1263.4 158% 534.9 18.94 0.35% 1.89% 1.3 1.2 1.1 0.06 0.2
2146.0 1257.7 138% 986.8 18.90 0.35% -0.88% 1.4 1.3 1.3 0.07 0.2
2071.9 1261.0 159% 676.3 17.27 -0.44% -1.99% 1.6 1.5 1.5 0.09 0.2
2056.1 1260.5 133% 1225.1 17.27 -0.80% -1.97% 1.8 1.8 1.7 0.10 0.2
250m resolution, TDI = YES, Upper = BOL(COLD) / Lower = EOL(HOT)
IFOV
250m
250m
340
340
300
300
Noise
Sigma (max) NEdT [K]
Spec.
(500m)
Ch
SWI-1
Gain
Sigma (max)IFOVBand
Width
Spec.
Lmax Lstd Linearity Error (max)Gain
(min)Dark
Signal Level (min)
SNR
Noise
Chλc
Band
Width
Gain
[micron]
Signal Level (min) Back
GroundTmax Tstd Gain
300K
Error (worst)
SWI-2
λc
10.78 0.74
TIR-2 11.97 0.77
TIR-1
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
See details at SGLI Sensor Characterization homepage, http://suzaku.eorc.jaxa.jp/GCOM_C/data/prelaunch/index.html
11
Initial Check Outpurpose
Confirmation of the all sensor function• Works properly as designed, and as tested in pre-launch tests. • Special calibration parameters were also checked.
not only nominal configuration and signal levels but also different ones binning rate, raw resolution mode, different LED configuration, integration time dependence and intermediate tilt angle … etc.
• For example, CCD integration time is fixed for the earth observation. Check various integration time effects which includes the ground
system processing algorithms, such as a stray light correction.
Obtaining the initial sensor performance data.• SGLI performance will degrade gradually for 5 years on-orbit lifetime. • Initial performance is very important for the succeeding calibration activity. • SGLI was turned on for the first light image on Jan. 1, 2018 (Y+9days)
30 days earlier than previous GLI sensor (Y+40days).• The solar angle calibration maneuver was conduced on Jan. 4, 2018 (Y+12
days).
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
12
Initial Check Outresults
Initial check out activities✓ Earth Observation✓ Onboard calibrator
• LED and lamp calibration• Solar calibration• Dark signal calibration• Black body calibration
✓ Calibration maneuver• Solar angle dependency• CCD de-striping• Lunar calibration
✓ Geometric calibration
All sensor functions were confirmed. The initial calibration parameters were obtained.
Approval to proceed to the initial Cal./Val. phase on March 28, 2018. Next target is the data release in December 2018.
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
13
Solar Reflective bandsVNR and SWI
Solar reflective bands trend for 9 months✓ Same solar diffuser degradation at both LED and Sun Calibration is
observed for VNR wavelength.✓ Detailed analysis and a comparison with other results is ongoing.
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
65%
70%
75%
80%
85%
90%
95%
100%
105%
2018/01/01 2018/04/01 2018/06/30 2018/09/28
VNR LED Cal Trend
NP-L VN01 NP-L VN02 NP-L VN03 NP-L VN04 NP-L VN05
NP-L VN06 NP-L VN07 NP-L VN08 NP-L VN09 NP-L VN10
NP-L VN11 S09(+60) PL-1 S09(+60) PL-2 Monitor PD-1 Monitor PD-2
65%
70%
75%
80%
85%
90%
95%
100%
105%
VN
01
VN
02
VN
03
VN
04
VN
05
VN
06
VN
07
VN
08
VN
09
VN
10
VN
11
PL-
1
PL-
2
PD
-1
PD
-2
PD
-3
PD
-4
NP-L S09(+60) Monitor
VNR LED Trend
65%
70%
75%
80%
85%
90%
95%
100%
105%
2018/01/01 2018/04/01 2018/06/30 2018/09/28
VNR SunCal Trend
NP-L VN01 NP-L VN02 NP-L VN03 NP-L VN04 NP-L VN05
NP-L VN06 NP-L VN07 NP-L VN08 NP-L VN09 NP-L VN10
NP-L VN11 S10(±0) PL1 S10(±0) PL2 Monitor PD-1 Monitor PD-2
65%
70%
75%
80%
85%
90%
95%
100%
105%
VN
01
VN
02
VN
03
VN
04
VN
05
VN
06
VN
07
VN
08
VN
09
VN
10
VN
11
PL1
PL2
PD
-1
PD
-2
PD
-3
PD
-4
NP-L S10(±0) Monitor
VNR SunCal Trend
65%
70%
75%
80%
85%
90%
95%
100%
105%
2018/01/01 2018/04/01 2018/06/30 2018/09/28
SWI Halogen Trend
Halogen Trend SW1 Halogen Trend SW2
Halogen Trend SW3 Halogen Trend SW4
65%
70%
75%
80%
85%
90%
95%
100%
105%
SW1 SW2 SW3 SW4
Halogen Trend
SWI Halogen Trend
14
Thermal band (TIR) performance
Two key technologies for TIR✓ 55K cooler system ✓ PV-MCT detectors
55K cooler system✓ 50W class Stirling cycle mechanical linear cooler ✓ Open type cryogenic dewar✓ Contamination control from manufacturing until launch✓ Outgas and cooler activation✓ Life time prediction
TIR observation performance✓ Gain stability✓ Low noise✓ Background thermal emission✓ Deselection of poor performance sub-pixel✓ Gain trend
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
15
55K Cooler SystemWith 50W class cooler
3:00:000.125
3:00:000.125
0
50
100
150
200
250
300
0 200 400 600 800 1000 1200 1400 1600 1800 2000
Rep
lace
men
tH
eate
rLo
ad[m
W]
,Co
ole
r P
ow
er [
W]
,Dew
arte
mp
[deg
C]
Days from Cool Down (2018/01/28)
ReplacementHeater Load[mW] Cooler Power
Adjustment @ Y+3years (TBD)
▽
△2018-09-08 (7months)
Required Lifetime(> 5 years)
▽
Cooler Power[W]
Dewar temp.[deg C]
36 W
37 W
38 W
39 W
40 W
life time preditionsbased on cooler power tunning
0
50
100
150
200
250
300
350
06:00:00 07:00:00 08:00:00 09:00:00
IR0593 IRS CCE TMP1 K IR0594 IRS CCE TMP2 K
Dewar Temp[K]
▽CoolDown Start
45
50
55
60
08:00:00 08:20:00 08:40:00 09:00:00
IR0593 IRS CCE TMP1 K IR0594 IRS CCE TMP2 K
IR0565 IRS LWIRD TMP1 K
Cold Stage
Cold Chip
09:00:00 12:00:00 15:00:00 18:00:00 21:00:00
IR0593 IRS CCE TMP1 K IR0594 IRS CCE TMP2 K
IR0565 IRS LWIRD TMP1 K
LWIRD Temp
0
50
100
150
200
250
300
350
400
450
06:00:00 07:00:00 08:00:00 09:00:00
IR0597 IRS CCE HTR PWR MON mW
ReplacementHeater Load[mW]
0
50
100
150
200
250
300
350
400
450
08:00:00 08:20:00 08:40:00 09:00:00
IR0597 IRS CCE HTR PWR MON mW
09:00:00 12:00:00 15:00:00 18:00:00 21:00:00
IR0597 IRS CCE HTR PWR MON mW
LWIRD Turned On
▽
0
10
20
30
40
50
06:00:00 07:00:00 08:00:00 09:00:00
IR0589 IRS CCE STC PWR MON W
Cooler Power[W]
0
10
20
30
40
50
08:00:00 08:20:00 08:40:00 09:00:00
IR0589 IRS CCE STC PWR MON W
09:00:00 12:00:00 15:00:00 18:00:00 21:00:00
IR0589 IRS CCE STC PWR MON W
Cooler system initiated on January 21, 2018. ✓ Continuous cooling starts on January 28, 2018.✓ All performance is fine. Enough margin for 5 years operation.
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
16
TIR performanceOrbit cycle
TIR-1 GAIN
0.45% p-p
Deep Space
Offset 1.30 Kp-pDeep Space Noise
1σ = 0.06KBlackbody
Offset 3.12 Kp-p
Blackbody Noise
1σ = 0.06K
TIR-2 GAIN
0.21% p-p
Deep Space
Offset 1.44 Kp-pDeep Space Noise
1σ = 0.08KBlackbody
Offset 3.17 Kp-p
Blackbody Noise
1σ = 0.08K
1 rev = 100min,
14 rev. (= 1day) plot for an orbit cycle repeatability for 250m mode✓ Gain is corrected and stable as designed.✓ Noise is low as tested in pre-launch test.
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
17
TIR performanceGain trend for 7 months
7months gain trend for 250m mode✓ Small degradation is observed
(TIR-1/11micron : 0.2%, TIR-2/12micro : 0.5%)✓ Enough margin for 5 years operation✓ Deselection technique to eliminate a poor performance sub-pixels works as
designed with periodical health check (3months : TBD)
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
18
Lunar Calibration
Lunar Model✓ GIRO/ROLO model✓ Earth-Moon distance, phase angle effect, liberation effect✓ Full Disc irradiation calibration
Sensor radiometric performance✓ Traceability to the national standards through pre-launch IS calibration✓ Sensor stability, offset correction, noise, radiation effects (protons)✓ Wavelength response function
Sensor geometric performance✓ Attitude rate, off-nadir attitude profile✓ Solid angle of each observation sample✓ VNR-CCD signal integration time effect✓ Optical distortion, MTF effects✓ IRS wisk broom scan profile with 45deg folding mirror effect✓ Low pass filter (LPF) effects
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
19
37. 16 msec
↑
Orbi t Cycl e 6,057 secOrbit Vel. 5.944E-2 deg/sec
7.444 km/secRaw Det 13 μmfocal len 166 mm
Overlap 76.3% Overlap 0.0%
Manouver Pitch Rate Equivalent obs angle rate
1.499E-1 deg/sec 4.829E-4 deg/sec (Note 2)
Note 1) Int Time = 255 case Note 1) Int Time = 255 case
Note 2) Calc. of sat movement, not angle rate calc.
radius 1,738km 37.164 msecdiameter 3,476km 1.499E-1 deg/sec
92. 9 line
28. 8 pix
Full Disc Irrradiance
21. 17arcsec 125. 0met er
5. 01ar csec 62. 5m
AT 4pix BINNING AT 4pix BINNING
msec
69. 2 meter
16. 15 arcsec
9. 291
Moon
Ear t h
798km
0. 52deg
( 356,565 ~ 384,873km = 7.4% ̂2 = 14.2 %)
384, 873km( 796 ~ 836km )
Moon SGLI
AT di r ect i on
Earth ObsSolidAngle
Lunar CalSolidAngle
CentroidCentroid
Movement
RAW Pix
0 10 20 30 40
arcsec
Before BINNing
After Binning
0 100 200 300 400
meter
Before BINNing
After BINNing
a) Less MTF performancecomaring to Earth Obs.
250m Pix
0.00 0.01 0.02 0.03 0.04
[deg]
Integral irradiance
Square Response
b) Integral response is equivalent to the square reponse assumption.c) Actual preceise solid angle calcuration is required to get the full disc irradiance.
Solid angle of each obs. sampleVNR-CCD signal integration time effect
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
20
EO case:(0.35 deg / scan)
LUCA case:(0.1 deg / scan)
-0.6
-0.5
-0.4
-0.3
-0.2
-0.1
0.0
40.340.440.540.640.740.840.9
AT[deg]
CT [deg]
SWI-01 Sample-1 SWI-01 Sample-2 Next Scan
1st Sample
Scan
Next Scan
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
-0.3-0.2-0.10.00.10.20.3
AT[deg]
CT [deg]
SWI-01 Sample-567 SWI-01 Sample-568 Next Scan
Det-01
Det-05
Scan Scan
0.05
0.15
0.25
0.35
0.45
0.55
0.65
-41.4-41.3-41.2-41.1-41.0-40.9-40.8
AT[deg]
CT [deg]
SWI-01 Sample-1145 SWI-01 Sample-1144 Next Scan
Last Sample
Scan
Next Scan
-0.6
-0.5
-0.4
-0.3
-0.2
-0.1
0.0
40.340.440.540.640.740.840.9
AT[deg]
CT [deg]
SWI-01 Sample-1 SWI-01 Sample-2 Next Scan
1st Sample
Scan
Next Scan
-0.3
-0.2
-0.1
0.0
0.1
0.2
0.3
-0.3-0.2-0.10.00.10.20.3AT[deg]
CT [deg]
SWI-01 Sample-567 SWI-01 Sample-568 Next Scan
Det-01
Det-05
Scan Scan
0.05
0.15
0.25
0.35
0.45
0.55
0.65
-41.4-41.3-41.2-41.1-41.0-40.9-40.8
AT[deg]
CT [deg]
SWI-01 Sample-1145 SWI-01 Sample-1144 Next Scan
Last Sample
Scan
Next Scan
Simple NearestNeighbor methodcause a significanterror because ofcomplexed geometry.The precise solid angle and overlap calculation should be used.
the scanning overlap effects by 0.74sec scanning cycleEO case : sat. moves 0.74sec x 7.4km/sec ÷ 798km 0.35 deg/scanLUCA case : sat. att. rate 0.1499deg/sec x 0.74sec 0.1 deg/scan
Difference between earth observation (EO) and lunarcalibration (LUCA) geometry for 45deg folded wisk broom
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
21
Solid Angle CorrectionUsing optical distortion model and satellite attitude model
GIRO/ROLO model comparison
Lunar Calibration Analysis
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
22
Preliminary results✓ VNR observed irradiance is 5-10% higher than GIRO model.✓ Small degradation (~1%) is observed in short wave length (380nm
and 412nm)✓ Calibration Difference in dual band channels (RED and NIR) Comparison with other results and PL/SWI calculation is ongoing.
Preliminary ResultsFor 7 months trend
First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
102%
107%
112%
VN01 VN02 VN03 VN04 VN05 VN06 VN07 VN08 VN09 VN10 VN11
Irr_Obs ÷ Irr_ROLO
380nm & 412nm
O2A absorption
channel
Dual Gain
channels
RED
NIR
short wave
degradation?~ 1%
102%
107%
112%
VN01
VN02
VN03
VN04
VN05
VN06
VN07
VN08
VN09
VN10
VN11roll=+1deg
Int. Time is longer
roll=0deg0.00
0.10
0.20
300nm 400nm 500nm 600nm 700nm 800nm 900nm 1000nm
refl
ecta
nce
[-]
ROLO_smooth_spectra ROLO spectr VN01VN02 VN03 VN04VN05 VN06 VN07
VN
1
VN
2V
N3
VN
4
VN
5V
N6
VN
7/V
N8
VN
10
/VN
11
VN
9
Conclusion On-orbit commissioning activities of SGLI during the first several
months to confirm the system integrity.
Technical aspects of the lunar calibration and the thermal infraredperformance.
All SGLI observation performance is confirmed as designed and astested in pre-launch test campaign.
Detailed calibration factor is under analysis.
The observation data will be delivered to the public after its reviewboard approval, in December 2018.
SGLI related information can be found at:
http://suzaku.eorc.jaxa.jp/GCOM_C/index.html
23First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
Acknowledgement SGLI Lunar calibration data was evaluated using the GSICS lunar
calibration tool (GIRO: GSICS Implementation of the Robotic LunarObservatory).
The authors would like to thank the GIRO implementationagencies led by EUMETSAT and GSICS lunar calibrationcommunity for GIRO usage and technical assistance.
24First year on-orbit cal activities of SGLI, Sep 26, 2018 SPIE Hawaii 2018
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