Development status of theSecond - generation Global
Imager (SGLI) on GCOM-C1

January 13, 2010
GCOM PI Workshop
Kazuhiro Tanakaa, Yoshihiko Okamuraa,
Takahiro Amanob, Masaru Hiramatsub,
Koichi Shiratamaba Japan Aerospace Exploration Agency(JAXA)b NEC TOSHIBA Space Systems Ltd.

Contents
1. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
4. BBM Test Results
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 20102

1. GCOM MISSION and BACKGROUND
9 GCOM Mission
9 GCOM Contribution
9 GCOM Background (ADEOS and ADEOS-II)
9 SGLI on GCOM-C1 satellite
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
4. BBM Test Results
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 20103

Global Change Observation Mission(GCOM)
 Global observation satellite system as JAXA’s GEOSS contribution.
 2 satellite series for 5 years, total 13 years observation.
9 GCOM-W Microwave radiometer observation for WATERCYCLE using AMSR2 (AMSR-E follow on)
9 GCOM-C
Optical multi-channel observation for RADIATIONBUDGET and CARBON CYCLE using SGLI (GLI follow on)
GCOM-C(CLIMATE)
GCOM-W(WATER)

Sensor

AMSR2

SGLI

Advanced Microwave Radiometer 2(AMSR2)
Passive Microwave Observation
Water vapor, soil moisture etc

Development status of SGLI at GCOM PI Workshop Jan. 2010

SensorSecond Generation Global Imager(SGLI)
Optical Observation 380nm – 12 micron
Cloud, Aerosol, Vegetation, Chrolophl etc

4

GCOM Contribution
GCOM observation
GCOM-W

Model prediction
GCOM observation

GCOM-C

Radiation budget•Surface albedo•Snow ice
•Cloud/ aerosol•SST/ LST

Input

Carbon cycle

Comparison•Vegetation cover•Primary production•Coastal environment
Frequent and longterm (>10yer) global
observation system

Prediction results

Climate system model

Water cycle•Water vapor, cloud,precipitation•Soil moisture•Sea ice, snow
•SST, wind

Improveaccuracy• Improvement of parameterization
about radiation budget and carbon
cycle, etc. in climate prediction
model.
• Verification and improvement ofprediction of the earth environmentchange including the water cycle bycomparison with the satellite
observation.

•Surface temperature•Sea level•Snow and sea ice area
•Environmental change•Rain/drought
distribution•Extreme weather
frequency•Land cover
Air temperature prediction

3°C

Data application

Knowledge

Future prediction

Operational use for fishery, searoute, weather forecast, etc.

monitoring and understanding of
the earth environment change

Policy design throughprediction improvement

Development status of SGLI at GCOM PI Workshop Jan. 2010

5

GCOM Background(ADEOS, ADEOS-II) GCOM is follow on program of ADEOS and ADEOS-II.
 Based on ADEOS-II operational anomaly, satellite development policy was
discussed at Space Activity Committee (SAC) of Japanese government.
 GCOM mission as a successor of ADEOS-II was re-evaluated.
Æ SGLI on GCOM-C1 satellite (SINGLE MISSION).
AMSR

GlobalImager
(GLI)

AMSR2

ADEOS-IIDevelopment status of SGLI at GCOM PI Workshop Jan. 2010

SGLI-VNR

GCOM-W series

SGLI-IRS

GCOM-C series
6

SGLI
on GCOM-C1 satellite
SGLI IRSELUSGLI VNR
ELU+X
flight direction

Y

deep
space

SGLI IRSSRU

SGLI VNR
SRU

+Z

earth

Development status of SGLI at GCOM PI Workshop Jan. 2010

SGLI
VNR
IRS
SRU
ELU

Second Generation Global Imager
Visible and Near Infrared Radiometer
Infrared Scanning Radiometer
Scanning Radiometer Unit
Electronic Unit7

1. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
9 Second Generation Global Imager (SGLI)
9 Technology background of SGLI
9 SGLI Specification
9 Observation Intervals
3. SGLI Observation Mechanism
4. BBM Test Results
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 2010

8

SGLI
Second Generation Global Imager
TIR-DET→
Non Polarized
Observation Telescopes(24deg FOV x 3)

←SWI-DET
Solar
Diffuser

Polarized
Observation
Telescopes(55deg FOV
x 2)

Earth
View Window←Optics

Sun Cal.
Window

Inside←Scan Mirror

About
1.4m

About
1.3m

About
1.7m

Visible and Near Infrared Radiometer(SGLI-VNR)

Sensor Unit

About
0.6m

Deep
Space
Window

Infrared Scanning Radiometer(SGLI-IRS)

SGLI IRS
Bread Board Modelfeatures

SGLI VNR

Non Polarized Observation （11ch）, IFOV 250m, Swath 1150km
Polarized Observation（2ch）, IFOV 1km, Swath 1150km

SGLI IRS

Shortwave Infrared （SWI 4ch）, IFOV 250m/1km, Swath 1400km
Thermal Infrared （TIR:2ch）, IFOV 500m, Swath 1400km

Development status of SGLI at GCOM PI Workshop Jan. 20109

Visible and Near infrared radiometer
SGLI-VNR VNR non Polarized Obs. (NP)– 3 telescopes with 24deg FOV realize thetotal 70 deg FOV Observation (1,150km)– Wide wavelength range Observation from380nm to 868.5nm.

NP Obs.
Sub-Unit

3 telescopes
for total 70deg FOV

 VNR Polarized Obs. (PL)– 2 telescopes with 55deg FOV each for673.5nm and 868.5nm Observation.
– AT tilting mechanism for +/-45deg– 55deg FOV with 45deg tilting corresponds
to 1,150km swath.

673.5nm telescope& 868.5nm telescope±45degtilting motor

BBM
NP telescope
Development status of SGLI at GCOM PI Workshop Jan. 2010

PL Obs.
Sub-Unit
AT : Along Track Direction
CT : Cross Track Direction

10

Infrared Scanning Radiometer
SGLI-IRS 45deg folding mirror rotates
continuously at 81rpm(740msec/rev) to observe “Earth– Solar Diffuser – Black Body –LED lamps – Deep Space”.
 Observation light through Ritchey
Chretien type telescope is divided
for two wavelength region.
OBS Light

SWI-DET

SCAN
MOTOR

OpticalBench

Sterling
CoolerBLACK
BODY

TIR-DET
Development status of SGLI at GCOM PI Workshop Jan. 2010

9 Shortwave Infrared detector(SWI-DET)
9 Thermal Infrared detector (TIRDET).

 SWI-DET uses InGaAs typedetectors at -30deg C using
peltier cooler.
 TIR-DET uses PV-MCT typedetectors at 55K using
mechanical stirling cooler.

11Technology background of
SGLI
Whiskbroom (Scanning Mirror)
MOS-1
VTIR

ADEOS
OCTS

ADEOS-II
GLI

4 Bands
0.5～12μm

12 Bands
0.41～12μm

36 Bands
0.38～12μm

OBSERVATIONTECHNOLOGY

SGLI
IRS
6Channels
1.1～12μm

Push Broom (CCD)
OBSERVATION

MOS-1
MESSR

JERS-1
VNIR

ADEOS
AVNIR

ALOS
AVNIR-2

4Bands0.5～1.1μm

4Bands
0.5～0.9μm

5Bands
0.4～0.9μm

5Bands
0.4～0.9μm

ASTER
VNIR

TECHNOLOGY

SGLI
VNR
NP Observation
11 channels
0.38～0.87μm
PL Observation
2 channels
0.68, 0.87μm

4Bands
0.5～0.9μm

SGLI uses both
Whisk Broom andPush Broom type
Sensor Heritage
Development status of SGLI at GCOM PI Workshop Jan. 201012

SGLI Specification• The SGLI features are 250m (VNR-NP & SW3) and 500m (TIR) spatial resolution
and polarization/along-track slant view channels (VNR-PL), which will improve
250m over the Land or coastal
land, coastal, and aerosol observations.
area, and 1km over offshore
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. for674nm 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 bymasked pixels and nighttime obs.
SW: Solar diffuser, LED, Lunar, and darkcurrent by deep space window
T: Black body and dark current by deep
space window

SGLI channels
Lstd
Lmax SNR at Lstd IFOV
VN, P:
VN, P, SW:
VN, P, SW: nm
2
SNRm
W/m /sr/μm
T: μm
T: Kelvin
T: NEΔT
380
10
60
210
250
250
412
10
75
250
400
250
443
10
64
400
300
250
490
10
53
120
400
250
530
20
41
350
250
250
565
20
33
90
400
250
673.5
20
23
62
400
250
673.5
20
25
210
250
250
763
12
40
350
1200
250/1000
868.5
20
8
30
400
250
868.5
20
30
300
200
250
673.5
20
25
250
250
1000
868.5
20
30
300
250
1000
1050
20
57
248
500
1000
1380
20
8
103
150
1000
1630
200
3
50
57
250
2210
50
1.9
20
211
1000
10.8
0.7
300
340
0.2
250/500
12.0
0.7
300
340
0.2
250/500
λ

CH
VN1
VN2
VN3
VN4
VN5
VN6
VN7
VN8
VN9
VN10
VN11
P1
P2
SW1
SW2
SW3
SW4
T1
T2

Δλ

optionDevelopment status of SGLI at GCOM PI Workshop Jan. 201013

SGLI Spectral Channels
Specifications of SGLI, such as center wavelengths, band width, SNR, anddynamic range, are designed in consideration of retrieval
algorithms of the observation targets.
IRS channels

VNR channels

.

.

.

.

Blue GreenRed
Yellow.

.

.

Development status of SGLI at GCOM PI Workshop Jan. 201014

Observation Frequency
 GCOM-C1 orbit is“34days repeat orbit”
with “3.8days quasi
repeat cycle”.

350km

ALOS SCAN-SAR OBS（Jan. 28, 2009）

ALOS AVNIR-2 OBS(Feb. 24, 2009）

70km

1150kmÆ Any point on the equator canbe observed at average 2.4
days frequency.
Æ Average 2 days frequency
observation is possible for
middle latitude. (35deg)

SGLI-VNR 1,150km（MODIS Jan. 28, 2009）

SGLI-IRS 1,400km

1400km（MODIS Jan. 28, 2009）SGLI VNR 1day OBS Area
（GLI OBS Mar. 20, 2003）
2003）
Development status of SGLI at GCOM PI Workshop Jan. 201015

Observation Frequency
 GCOM-C1 ground trace distance at equator is 2,809km/rev and 743 km/day.
Æ SGLI-VNR with 1,150km swath (70deg FOV) realizes 94% global coveragefor 3 days at equator.
Æ Average 100% coverage per 2 days at middle latitude.
2,809km/rev
0km

1000km2000km

3000km0day

1day

743km/day
2day

Average OBS Freq. [day/1 time]-3000km -2000km -1000km

Average 2.4days Freq.
at equator

3.0
2.5

Average 2days Freq.
at 35deg latitude

2.0
1.5
FOV 70deg

1.0

FOV 80deg

0.5

height 798km(M=34, N=14, L=9)

0.0
0

3day

60

90

OBS lattitude [deg]2,636km/3day≒ 94% coverage

4day

5day

30

1,150km
OBS SwathAlt 798km, Cycle 3.8days (34days), FOV=70deg<- EastDevelopment status of SGLI at GCOM PI Workshop Jan. 2010

West ->

 GCOM-C1 orbit is 34 dayrecurrent orbit.
Æ 13 Cross Trackdirectional observation
per 34 days is possible.
161. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
9 VNR Non Polarized Observation Focal
Plane Assembly
9 VNR Polarization Observation
9 TDI mode observation of TIR detectors
9 Data Acquisition Scenario
9 Onboard calibration
4. BBM Test Results
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 201017

VNR Non Polarized Obs.
Focal Plane Assembly Each NP telescope is equipped withindependent Focal Plane Assembly.
 To realize 11ch observations of VNRNP telescope, 11 lines long Band Pass
Filter (BPF) is mounted on 11 line
CCD.

Block
FILTER

Band PassFILTER

11 ChsFilterAssy.

 Channel location and spectral non
uniformity requirement is set basedon detailed mission analysis such as
O2A band observation by EORC
scientists.
ChannelLocation

ocean gain channels

CCD

land gain channels

satellite flight direction Æ

Development status of SGLI at GCOM PI Workshop Jan. 201018

VNR Polarization Observation
 Intermediate scattering direction (60-120deg) should be observed for aerosol
retrieval with +/- 45deg tilting radiometer. Tilt angle will be switched bycommand depending on this scattering angle requirement.
9 Backward Looking
Required Scattering Angle
9 Forward Looking
60 – 120deg
9 Nadir Looking (optional)
 3 directional linear polarizer on FPA
realize Stokes parameter observation
Solar Light(I, Q, U components)
Forward Looking(+45deg)

Nadir Looking(0deg)

Backward Looking(-45deg)

180

Back
Scattering

scattering angle [deg]150

Backward
Looking120

Forward
Looking

Forward
Scattering

120deg

90

60

60deg

30

Forward
Looking

ForwardNadir

Backward
Looking

Backward

0
-90

SOUTH

-60

-30
0
30
solar lattitude at obs point [deg]satellite orbit direction

60

90

NORTH

Development status of SGLI at GCOM PI Workshop Jan. 2010

satellite direction

19

TDI mode observationof TIR detectors
 TIR-DET works with Time Delayed Integration (TDI) mode.
Æ Each 500m Observation channels consists of 250m Ch-A and Ch-B.
Æ Optional 250m Observation is possible.
PWR&CONTROL
Ch-B
Ch-A

T1

T2
500m Obs Mode

t0

t0+⊿t

Scan
Direction

①
②
③

⑤

④

⑥

t0

t0+⊿t

⑦

t0+2⊿t⊿t= 250mSampleInterval

250m Obs Mode (Option)①②

t0+2⊿t

⑧

500m

TDI

500m

TDI

500m
750m

250m resolution
20detector/ch

500m

T2 Ch-B OUT
T2 Ch-A OUT
T1 Ch-B OUT
T1 Ch-A OUT

Development status of SGLI at GCOM PI Workshop Jan. 201020

Data Acquisition Scenario ALL 19 Channels observation for Day Mode 250m/500m resolution data for Land, 1km for Ocean
 TIR & SW（1.6 & 2.2 micron ; Land） for Night Mode.

 BASIC Observation
Concept Æ
DAY
1km

NIGHT
250m

DAY
250m

NIGHT
1km

250m Obsfor Day Mode
Land Area(21.0Mbps)

DAY
1km

Development status of SGLI at GCOM PI Workshop Jan. 201021

Data Acquisition Scenario【SGLI-VNR
NPOBS
OBS】
VNR-NP【SGLI-VNR
OBS】
VNR-PL PL
OBS

1km
OBS
Forward
Looking
OBS

250m
OBS
LAND DAY

NIGHT

1km
OBS

DAY

STBY-2IRS-SWI【SGLI-IRSSWI OBS
OBS】

NIGHT

Backward
Looking
OBS

STBY-2

IRS-TIRTIROBS【SGLI-IRS
OBS】

1km
OBS

1km
OBS

250m
OBS

STBY-2LAND DAY

500m
OBS

NIGHT

陸

LAND

NIGHT

LAND
SW3 250m
SW4 1km

1km
OBS

DAY

1km
OBS

500m
OBS

STBY-2Development status of SGLI at GCOM PI Workshop Jan. 2010

22

SGLI-VNR
Onboard calibration
 Deployable Spectralon diffuser is used for both Solar and LED calibration.
Calibration coefficient will be traced using this solar calibration data.
 β angle dependency for solar calibration will be characterized shortly
after launch using satellite yaw manouver.

ele.

NP Tele.
Right

Tilt Mechanism
Deployed
Spectralon Diffuser

Diffuser Deploy
Mechanismwith safety function

PL telescope
Tilting Mechanism

Development status of SGLI at GCOM PI Workshop Jan. 2010

NP Tele.
CenterNP Tele.
Left

Te
le
.

P
P2 OL

NP Tele.
Right

NP Tele.
CenterNP Tele.
Left

P
P1 L Tele.
P
P2 L Tele.

Backward Tilting
PL telescopessm

LED and Monitor
Bench

oy ni
pl ha
De ec
M

oy m
pl is
De hanec

M

Tilt Mechanism

ite
Wh
D
E
L
R
NI
D
LE

P
P1 OL
T

n
lo
tra er
ec u sSp Diff

Sunnlo
tra er
ec u sSp Diff

LED CAL

Solar CAL23

SGLI-IRS
Onboard calibration
 IRS 81rpm rotating for both “Earth Observation” and “Calibration”.
TIR Calibration : “BLACK BODY” and “Deep Space”
SWI Calibration : “Diffused Solar Light”,
Spectralon
Diffuser
Calibration
Window“LED/Lamp”
and “Deep Space”
Light
Guide

Earth Observation

Spect
ralon

Diffuser+Z (Earth)

Light Guide

Diffused
Solar Light

Deep SpaceSCAN
MIRROR

Light
Guide

LED &
Lamp
Development status of SGLI at GCOM PI Workshop Jan. 2010

+X
(Sat. Velocity) +Y(Space)

LE
D

/L
a
Li mp
gh C
al
t
.

BLACK
BODY

BLACK
BODY

24

1. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
4. BBM Test Results
9 Breadboard Model (BBM) activity
9 BBM test results of VNR
9 BBM test results of IRS
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 201025

Bread Board Model (BBM) Activity

Visible and Near infrared radiometer (VNR)
CriticalTechnologies- To Validate
feasibility of
the criticalcomponents

BBM
System Design-To establish SGLI

system design toachieve observation
requirement

BBM Component Tests

BBM System Tests- To assess and demonstrate theobservation performances by component
level- To assess and demonstrate
the observation performancesby system level<Major BBM component>

Radiometric Tests

・11line CCD・Bandpass filter AssemblyNP
Sub-Unit
・Optics

VNR-NP・Polarization filter Assembly

Geometric Tests

・Bandpass filters
VNR
SRU

・Readout Circuit
VNR-PL

Tests with onboard
calibrators

・CCD

Complete

Complete

Development status of SGLI at GCOM PI Workshop Jan. 2010

Complete

Complete26

Bread Board Model (BBM) Activity
Infrared Scanning radiometer (IRS)

CriticalTechnologies- To Validate
feasibility of
the criticalcomponents

BBM
System Design-To establish SGLI

system design toachieve observation
requirement

BBM Component Tests- To assess and demonstrate theobservation performances by component
level<Major BBM component>
・SWIR Detector

・TIR Detector

BBM System Tests- To assess and demonstrate
the observation performancesby system level

SWIR Radiometric Tests

BBM用
SWI検知器・Optics
・Mechanical Cooler

IRS
SRU

TIR Radiometric Tests(Vacuum condition)

・Scan Mirror Assembly・Mirror Sample
観測光

SWI検出器
DET

走査
モータ

光学
ベンチ

・CCD
・TIR detector

・Readout Circuit

Geometric Tests

・Blackbody

黒体

Tests with onboard
calibrators

TIR検出器DET

IRS Optical Bench

Complete

Complete

Development status of SGLI at GCOM PI Workshop Jan. 2010

Complete

Complete
27

BBM test results of VNR
Dynamic Range VNR dynamic range requirement is set based on careful study of target
characteristics.
 VNR uses CCD. Integration time can be easily changed by command.
 This means dynamic range adjustment is possible.
9 Difference between design and manufacturing results such astransmittance of optics can be adjusted
9 Dynamic range can be changed by command even after launch
9 Calibration technique using different integration time.

Development status of SGLI at GCOM PI Workshop Jan. 2010

28

BBM test results of VNR
CCD Integration Time
Previous GLI design

SGLI VNR design

Development status of SGLI at GCOM PI Workshop Jan. 2010

29

BBM test results of VNR
Linearity

Development status of SGLI at GCOM PI Workshop Jan. 2010

linearity error

test result of VN10 non-polarized observing telescope
4%
3%
2%
1%
0%
-1%
-2%
-3%
-4%

test result
linearity req
0linearity error [%] Linearity is very important forradiometer because it leads toaccuracy dependencies to input
radiance level.
 Also, the test methodology
using integration time above
mentioneduses
theassumption that sensor is very
linear.
 VNR BBM linearity is checked
for
both
input
radiance
dependencies and integration
time dependencies.
 Test result is very good andfurther detailed analysis isconducted to find the major
non-linear element to improve.

10
9
8
7
6
5
4
3
2
1
0

10

20
30
input radiance [W/m^2/str/μm]
test result of non-polarized observing telescope

40

0deg
+12deg-12degreq

VN1 VN2 VN3 VN4 VN5 VN6 VN7 VN8 VN9 VN10 VN1130

BBM test results of VNR
Noise SGLI noise performance is required as Signal to Noise Ratio(SNR) at standard signal observation radiance (Lstd) for
each observation channel.
 Both integration time dependence and input radiance for
SNR was checked.
 The all channels noise level met the sensor specification.
Test Result

6

Development status of SGLI at GCOM PI Workshop Jan. 2010

Ｐ1

VN11

VN10

VN08

VN07

VN06

0

VN05

25

1

VN04

10
15
20
iinput radiance [W/m^2/str/μm]

2

VN03

5

3

VN02

0

4

VN01

SNR
Lstd
fitting curve
Req at Lstd

Req

5

VN09

1000
900
800
700
600
500
400
300
200
100
0

7

rms noise [count]

SNR

test result of non-polarized observing telescope (VN10)

31

BBM test results of VNR
Polarized Light Observation
 The special polarization unit is set to the collimator light source. The
collimator polarization characteristic is canceled with de-polarizer filter
and polarized unit can be rotated around the optical axis to realize thedesired polarized direction for both linear and partially polarized light.
 As the result of BBM test, approximately 4% polarization observation
accuracy (ΔP/Pstd) and 1.3deg polarization direction error is confirmed
for the 670nm polarization observing telescope with standard 5%
polarized light (Pstd).
Polarization
Unit

VNR BBM

test result of 670P polarization observing telescope

Collimator
SystemRotating
Stage

Polarization AccuracyΔP/P

7%
6%

Design Target

5%

Input Angle

4%+27.5deg

3%+0.5deg2%-27.5deg

1%
0%
250

500

750

∞

SNR

Development status of SGLI at GCOM PI Workshop Jan. 2010

32

BBM test results of IRS
Scanning Performance

Histogram [%] Because very stable rotating speed is important for sensor observation geometry,the centroid position error and product of inertia should be minimized.
 Manufacturing error and assembly process were carefully studied and confirmed.
The friction learning technique in the rotation speed control loop is also applied.
 The selection of the bearing unit is another key issue for the IRS 5years operation
requirement. The bearing lifetime test under the vacuum condition was
successfully completed for required 2.7 x 10^8 revolution operation and still
under the test for the further design margin.

Position error [deg]Development status of SGLI at GCOM PI Workshop Jan. 2010

33

BBM test results of IRS
SWI Radiometric Performance

Test Result

6

0.6K

2

0.2K

1

0.1K

0

0.0K
T2

0.3K

T1

3

SW4

0.4K

SW3

4

SW2

0.5K

SW1

5

left axis

Development status of SGLI at GCOM PI Workshop Jan. 2010

Req

TIRrmsnoise NEdT [K]0.7K

7
SWI rmsnoise [count]

SNR performance
9 high transmittance of telescope
and filters
9 detector sensitivity
9 dark current of 2.2μm channel
at operating -30deg C
9 System SNR performanceDynamic Range
9 adjustment at analog signal
processor (ASP)
EMC allowance limit
9 Trans Impedance Amplifier (TIA)
for detector readout.
9 EMC test in the shield room forboth RF radiation and conductive
noise allowanceright axis

34

BBM test results of IRS
TIR Radiometric Performance Detector temperature & performanceÆ special dewar for 55K
Æ spectral characteristics at 55K
Æ detector linearity
 Effects of sensor temperature around
optical pathÆ dynamic range design considering
sensor temperature range
Æ Thermal vacuum test to confirm
the design.
Observation
light

SecondarymirrorPrimary
mirror Dynamic range adjustment
methodology
Æ integrating capacity at ROICÆ integration timeÆ post amplifier gain (fixed)
 TIR system level test meets the noise
requirement (NEdT). (previous page)

SWI
Detector

TIR
Detector
Scan
MirrorDichroic
filterRitchey-Chretien telescope

Development status of SGLI at GCOM PI Workshop Jan. 201035

1. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
4. BBM Test Results
5. Current Phase (EM Phase) Activity
9 Major issues for EM phase activity
9 SGLI EM phase activity
9 GCOM-C1 project status
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 201036

SGLI EM phase activity
 1st SGLI preliminary design review (PDR-1) was held on Dec. 22, 2009 2nd SGLI PDR (PDR-2) for CCD is planned for middle of Feb. 2010.
 Based on these design review SGLI BBM refurbishment and Engineering
Model (EM) manufacturing is under way.
 Full EM test is planned including environmental test, such as Vibration,
Shock and Thermal Vacuum Test.
Scanning
Radiometer
Unit
(SRU)

【EM Phase】【BBM Phase】 ▼SGLI PDR
BBM
Observation
Performance
Test

Refurbish

SRU TEST
including
Env. Test

SRU-ELU
I/F Test

MechanicalParts... etc
Electronics
Unit
(ELU)

ELU
(EM)

None

Manufacturing▲
NOW

Development status of SGLI at GCOM PI Workshop Jan. 2010

【PFM Phase】

FlightModel(PFM)Satellite
I/F Test
ELU TEST
including
Env. Test
Test▲
Summer 201137

Major issues
for EM phase activity
 The full EM test and evaluation is planned updated from the BBM test
results and items not tested in BBM phase.
 SGLI VNR + IRS
9 Contamination Strategy, Design, Analysis, Test and Evaluation
9 Electrical power consumption. Satellite anomaly case analysis.
9 SGLI operational design, such as normal TLM/CMD operation,
contingency plan and calibration manouver.
9 SGLI data processing requirement for Level-1 algorithm.
 SGLI VNR
9 Spectral non uniformity of Band pass filter for NP observation
9 Stray Light reduction
9 CCD blooming and diffusion
 SGLI IRS
9 TIR detector stability, cooler disturbance
9 SWI noise suppression, stray light reduction, polarization sensitivity
9 Scanning stability
Development status of SGLI at GCOM PI Workshop Jan. 201038

GCOM-C1 Project Status GCOM-C1 satellite design is on going. Main design focus is on the difference
between GCOM-W1 and GCOM-C1 satellite because of mission difference, suchas high data rate handling from SGLI.
 GCOM-C1 satellite system PDR is planned for June 2010.
 The target launch of GCOM-C1 is JFY2014 (TBD).
Japanese
Fiscal Year

JFY
2006

JFY
2007

JFY
2008

JFY
2009

JFY
2010

GCOM-W1 Project start

JFY
2011

JFY
2012

GCOM-C1 Project start

SDR

GCOM-W1

GCOM-C1

Phase-A

PDR

Phase-B

CDR

Phase-C

Phase-D

SDR
Pre-Phase-A

Phase-A

Development status of SGLI at GCOM PI Workshop Jan. 2010

JFY
2014

GCOMC1
Launch(TBD)

GCOM-W1
LaunchMilestone

JFY
2013

PDR
Phase-B

Phase-C

CDR
Phase-D39

1. GCOM MISSION and BACKGROUND
2. SGLI OVERVIEW
3. SGLI Observation Mechanism
4. BBM Test Results
5. Current Phase (EM Phase) Activity
6. Conclusion
Development status of SGLI at GCOM PI Workshop Jan. 201040

Conclusion
 GCOM is JAXA’s GEOSS contribution of global observation
for water cycle, radiation budget and carbon cycle.
 SGLI is the optical sensor on GCOM-C1 satellite.
 Bread Board Model (BBM) design and test activity has
successfully completed.
 1st SGLI PDR was held on Dec. 22, 2009. 2nd SGLI PDR isplanned for Feb. 2010. Engineering Model (EM)manufacturing is under way.
 The EM testing including environmental test and I/F testwith satellite system is planned.
Development status of SGLI at GCOM PI Workshop Jan. 201041