The development status of Second
Generation Global Imager (SGLI),
Infrared Scanning Radiometer (IRS)
October 14, 2014
SPIE Asia-Pacific, Beijing
Kazuhiro TANAKA
GCOM project/JAXA
http://suzaku.eorc.jaxa.jp/GCOM_C/index_j.html
Contents
GCOM mission and GCOM-C satellite
 Current Status
 The development status and key
components performance of Infrared
Scanning Radiometer (IRS)
 Conclusion

The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
2
Global Change Observation Mission
(GCOM)


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-C
(CLIMATE)
GCOM-W
(WATER)
AMSR2
GCOM-W “SHIZUKU”
was launched on May 18,
2012.
Sensor
Advanced Microwave Radiometer 2
(AMSR2)
Passive Microwave Observation
Water vapor, soil moisture etc
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
GCOM-C
is scheduled for launch
in JFY2016.
Sensor
SGLI
Second Generation Global Imager
(SGLI)
Optical Observation 380nm – 12 micron
Cloud, Aerosol, Vegetation, Chrolophl etc
3
Second generation Global Imager (SGLI)
on GCOM-C satellite
SGLI VNR
ELU
SGLI IRS
ELU
+Y
deep
space
+X
flight
direction
+ Z earth
SGLI VNR
SRU
SGLI IRS
SRU
Mission Life
> 5 years
Solar Paddle
> 4000w （End of Life）
Mass
about 2,000kg
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
SGLI
VNR
IRS
SRU
ELU
Second Generation Global Imager
Visible and Near Infrared Radiometer
Infrared Scanning Radiometer
Scanning Radiometer Unit
Electronic Unit
4
Current Status




Critical Design Review (CDR) of SGLI sensor and
GCOM-C satellite was held in 2013.
 The flight model (PFM) manufacturing was
approved.
The manufacturing of SGLI key flight parts, such as
optics, filters, detectors or coolers, is almost finished
and under the final inspection for the components
assembly and tests.
SRU sensor system integration and test is ongoing
until early 2015. The sensor level pre-flight tests will
be done in 2015.
Satellite level test will start in 2015 and planned for
launch in JFY 2016.
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
5
SGLI Performance
• The SGLI features are 250m (VNR-NP, SW3 & TIR) spatial resolution and
polarization/along-track slant view channels (VNR-PL), which will
improve land, coastal, and aerosol observations.
GCOM-C SGLI characteristics
Sun-synchronous
Orbit
(descending local time: 10:30)
Altitude 798km, Inclination 98.6deg
Mission Life 5 years (3 satellites; total 13 years)
Push-broom electric scan (VNR)
Scan
Wisk-broom mechanical scan (IRS)
1150km cross track (VNR: VN & P)
Scan width
1400km cross track (IRS: SW & T)
Digitalization 12bit
Multi-angle
Polarization 3 polarization angles for P
obs. for
674nm and
Along track Nadir for VN, SW and T,
869nm
direction
+45 deg and -45 deg for P
On-board
calibration
VN: Solar diffuser, LED, Lunar cal
maneuvers, and dark current by
masked pixels and nighttime obs.
SW: Solar diffuser, LED, Lunar, and dark
current by deep space window
T: Black body and dark current by deep
space window
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
250m over the Land or coastal
area, and 1km over offshore
SGLI channels


Lstd
Lmax
IFOV
NP,PL,SWI:
NP, PL, SWI:
CH NP, PL, SWI: nm
SNR at Lstd
W/m2/sr/m
m
T: m
T: NET
T: Kelvin
VN1
380
10
60
210
250
250
VN2
412
10
75
250
400
250
VN3
443
10
64
400
300
250
VN4
490
10
53
120
400
250
VN5
530
20
41
350
250
250
VN6
565
20
33
90
400
250
VN7
673.5
20
23
62
400
250
VN8
673.5
20
25
210
250
250
250/1000
VN9
763
12
40
350
1200
VN10 868.5
20
8
30
400
250
VN11 868.5
20
30
300
200
250
PL1
673.5
20
25
250
250
1000
PL2
868.5
20
30
300
250
1000
SW1
1050
20
57
248
500
1000
SW2
1380
20
8
103
150
1000
SW3
1630
200
3
50
57
250
SW4
2210
50
1.9
20
211
1000
T1
10.8
0.7
300
340
0.2
250/1000
T2
12.0
0.7
300
340
0.2
250/1000
TIR : 500m resolution is also used.
6
Infrared Scanning Radiometer
(SGLI-IRS)
Earth
Flight
direction
1.4m
Engineering model of SGLI-IRS
for vibration test configuration
OBS Light
0.6m
SWI-DET
SCAN
MOTOR
Optical
Bench
Sterling
Cooler
BLACK
BODY
Weight: 193kg
Power: 400W
TIR-DET
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
7
IRS scanning mirror

Reflectance [%]

45deg tilting folding octagonal mirror.
Mirror is coated aluminum with above 84% reflectance and
polarization ratio is less than 1.4% including the telescope
and SWI-BPF effects.
The effect of mechanical stress to the mirror flatness is
also considered with the light weight requirement (1.1kg).
100
100
95
95
90
90
85
85
80
80
Reflectance [%]

75
70
75
70
No.1
65
No.2
60
60
55
55
50
1.0
1.5
2.0
Scanning
Mirror (flight model)
No.1
65
No.2
2.5
[micron]
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
50
10
11
12
13
[micron]
8
IRS scanning mechanism




Scanning Mechanism
(flight model)
Control Error
25000
Resolver Calibration Accuracy
16000
14000
20000
σ=0.02pixel
1σ=0.07pixel
12000
15000
Histgram
10000
10000
8000
6000
4000
5000
2000
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
0.300
0.225
0.150
0.075
0.000
-0.075
-0.150
0.147
0.124
0.101
0.078
0.054
0.031
0.008
-0.016
-0.039
-0.062
-0.085
-0.109
-0.132
-0.155
[250m pixel]
-0.225
0
0
-0.300
Histgram
Geometric accuracy req. is 0.5 pixel of 250m.
High rotation stability and measurement accuracy.
AC servo motor with slot less type to avoid the torque
disturbance.
The low surface pressure bearing with the high reliability
lubrication.
250m pixel
9
IRS telescope




Ritchey-chretien type coated aluminum telescope.
(F/2.64, f=448mm, 170mm aperture)
The several optical shields optimized to prevent the
undesired stray light path.
Thermally controlled within narrow room temperature
range for 5 years operation
The minimum depth of focus is tested with MTF 60%
requirement.
OBS Light
FPA
Scan Mirror
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
IRS telescope
IRS telescope
(Flight Model)
10
SWI focal plane assembly (SWI-DET)
 InGaAs
type SWI PD array with 4band BPF.
 The detector array is cooled at -30deg using peltier
electronic cooler with PI control circuit in order to reduce
the dark signal of 2.2micron channel.
 TIA circuit designed for low noise readout.
 AR coated window and filled with Xeon gas.
SWI
4Band Filters
Window
4BAND
FILTER
4BAND PD
ARRAY
Flight
Model
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
Peltier
Cooler
11
TIR focal plane assembly (TIR-DET)
 PV
type MCT detector with cold BPF in the LWIRD filled
with Neon gas.
 Cooler assembly with cryogenic dewar for the 55+/-0.1K
with PI controlled heater.
Flight
Cryogenic
Model
Dewar
 140micron (250m) big pixel output using
28micron small pixel summation.
Cold Head
 Commandable selection table for poor
performance sub-pixel deselection.
A-MUX
ADD
Flight
Model
Compressor
ADD
250m(140micron)
x 20 pixels
Balancer
Video Signal
Selection Table
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
Long Wave Infrared
Detector (LWIRD)
Cooler Assembly
12
IRS spectral performance
700
Total Response [mA/W]
600
300
200
100
0
950
1000
1050
1100
500
400
300
200
100
0
1300
1150
1350
[nm]
0.8
0.6
0.4
0.2
0
9500
1500
TIR-1
10000
10500
[nm]
11000
11500
12000
11500
[nm]
12000
12500
13000
1.2
1000
900
800
600
500
400
300
200
100
1
SW4
Normalized spectral response
SW3
Total Response [mA/W]
Total Response [mA/W]
1450
[nm]
700
700
600
500
400
300
200
100
0
1450 1500 1550 1600 1650 1700 1750 1800
[nm]
SW1
SW2
SW3
SW4
T1
T2
1400
1100
900
800
1
SW2
Normalized spectral response
SW1
400
Total Response [mA/W]
1.2
800
500
0
2100
2150
2200
[nm]
2250
2300
2350
TIR-2
0.8
0.6
0.4
0.2
0
10500
11000
FWHM Spectral Reponse [nm]
Weighted Spectal Response
Center
Peak
Lower Half Response
Upper Half Response
band width
Center
Half Responce
band width
Wavelength Wavelength Wavelength
10-80%
Wavelength
10-80%
Wavelength
Lower
Heigher
width
width
Wavelength Wavelength
1054.9
1054.0
1044.4
11.1
1065.5
11.2
21.1
1054.9
1043.9
1065.7
21.7
1385.3
1387.0
1375.3
7.2
1395.4
7.6
20.1
1385.4
1375.0
1395.6
20.6
1633.7
1667.0
1536.2
19.4
1731.2
19.5
195.0
1634.5
1539.2
1730.2
191.0
2210.6
2207.0
2185.4
18.2
2235.8
16.7
50.4
2210.7
2184.8
2236.5
51.7
10782.7
10840.0
10415.0
197.9
11150.4
195.8
735.3
10786.1
10420.0
11157.1
737.1
11974.8
11790.0
11582.0
264.6
12367.5
289.0
785.5
11956.7
11559.1
12327.9
768.8
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
SGLI-N-TD-14119_0930_SGLI SWI 総合波長特性[第4版].xlsx
SGLI-N-TD-14238_0909_SGLI TIR 総合波長特性[第2版].xlsx
13
Black Body
 Black
body is used for thermal channels
calibration on-orbit with cold space response.
 The sensor background signal is canceled in two
points calibration techniques. The emissivity of
black body is better than 98%.
Earth Observation
Diffused
Solar Light
Deep Space
SCAN
MIRROR
Light
Guide
BLACK BODY
OPTICAL BENCH
BLACK BODY
(Flight Model)
2 points calibration for TIR and SWI
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
14
LED-Halogen light assembly



LED-Halogen light assembly is used to monitor the sensor
output between pre-flight calibration and on-orbit.
Relative spectral shape is only checked with halogen lamp
output. The absolute response comparison is by 1.6micron
LED output in SW3 channel.
SWI calibration activity is planned for every 8 days on orbit.
Calibration maneuver such as lunar calibration and solar
beta angle dependency check is also planned on orbit for the
reliable calibration.
1.0
Halogen
8.0V
10.0V
12.0V
0.9
SWI LED assembly
SWI LED PD
assembly
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
Relative response
0.8
SWI Halogen
assembly
9.0V
11.0V
0.7
0.6
0.5
0.4
0.3
0.2
0.1
0.0
1000
1200
1400
1600 1800
[nm]
2000
2200
2400
15
IRS integration and tests




IRS flight model sensor integration activity is ongoing.
All components and panels are thermally baked before
integration under thermal vacuum conditions to prevent
outgas effects to IRS optical system.
Optical bench with key optical components is located in
the middle of SRU baseplate.
Integration activity is planned
IRS-SRU
in 2014 autumn period, and
Preflight Test (PFT) including
Colimeter
optical performance check
starts at the end of 2014.
Rotation Stage
The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
16
Summary
SGLI flight model manufacturing is ongoing.
 Key IRS flight component test results are
presented.
 Sensor integration & test will be started within
this year.
 Target launch of GCOM-C is JFY2016.

The development status of SGLI-IRS, Oct 14, 2014, SPIE Beijing
17

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