Operation Concept of the Second
Second‐generation Global Imager(SGLI)
October 13, 2010
SPIE meeting in Incheon
Kazuhiro TANAKA*1, Yoshihiko OKAMURA*1
Takahiro Amano*2, Masaru Hiramatsu*2, Koichi Shiratama*2* Japan Aerospace Exploration*1li Agency ((JAXA))*2 NEC TOSHIBA Space Systems Ltd.

http://suzaku.eorc.jaxa.jp/GCOM_C/index_j.html

Global Change Observation Mission(GCOM)
 Global observation satellite system as JAXA’s GEOSS contribution.
 2 satellite series for 5 years,
years total 13 years observation.
observation
9 GCOM-W Microwave radiometer observation for WATERCYCLE using AMSR2 (AMSR-E follow on)
9 GCOM-C
GCOM CO i l multi-channel
Opticalli hl observation
b
i
f
for
RADIATION
BUDGET and CARBON CYCLE using SGLI (GLI follow on)
GCOM-C(CLIMATE)AMSR2GCOM-W
GCOM
W(WATER)

Sensor

SGLI

Advanced Microwave Radiometer 2(AMSR2)
PassiveP
i Microwave
Mi
Ob
Observationi
Water vapor, soil moisture etc

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

SensorSecond Generation Global Imager(SGLI)
O i l Observation
OpticalObi 380nm380– 12 microni
Cloud, Aerosol, Vegetation, Chrolophl etc

2

GCOM Contributions to GEOSSGCOM program
GCOM-W
GCOM-CGCOM
observation

RadiationbudgetCarboncycle
FrequentFreq
ent & longterm (>10yer)
observation

Model prediction•Surface temperature•Sea level•Snow and sea ice area
•Environmental change

Input•Rain/drought
distribution•Extreme weather
frequencyqy•Land coverComparison

Air temperature prediction

Climate system
y
model

Water
cycle

Prediction results

3°C

Data application

Knowledge

Future prediction

Operationaluse

monitoring andunderstanding

PolicyDicision

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

3

SGLI
on GCOM-C1GCOM C1 satellite
t llitSGLI VNR
ELU

SGLI IRS
ELU

+Y
deep
space

+X
flightdirection+ Z earth

SGLI VNR
SRU

SGLI IRS
SRU
Mission Life> 5 years

Solar Paddle> 4000w （End of Life）

Mass

about 2,000kg

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

SGLI
VNR
IRS
SRU
ELU

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

4

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

Solar
Diffuser

EarthView Windowd

Polarized
Observation
Telescopes(55deg FOV
x 2)

Sun Cal.
Window

About
1.4m

About
1.3m

About
1.7m

Visible and Near Infrared Radiometer(SGLI-VNR)

Sensor Unit

Deep
Space
Window

About
0.6m

Infrared Scanning Radiometer(SGLI-IRS)features

SGLI VNR

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

SGLI IRS

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

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

5

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, andd 1k
1km over offshore
ff hGCOM-C SGLI characteristics
Sun-synchronous
Orbit((descending
g 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. ffor
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 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 windowi dOperation Concept f the SGLI, SPIE Incheon, October 13, 2010

SGLI channels
Lmax SNR at Lstd IFOV
Lstd
VN, P, SW:
VN, P:
VN,, P,, SW: nm
2m
SNR
W/ /sr/μm
W/m
/ /
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
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

option6

Visible and Near infrared radiometer
SGLI VNR
SGLI-VNR VNR non Polarized Obs. (VNR‐NP)– 3 telescopes with 24deg FOV realize thetotal 70 deg FOV Observation (1,150km)– Wide wavelength range Observation from380nm to 868.5nm.
868 5nm

NP Obs.
Sub-Unit

3 telescopes
for total 70deg FOV

 VNR Polarized Obs. (VNR‐PL)– 2 telescopes
p with 55degg FOV each for673.5nm and 868.5nm Observation.
– AT tilting mechanism for +/‐45deg– 55degd FOV withh 45degd tiltinglcorrespondsdto 1,150km swath.

673.5nm & 868.5nm
telescope±45degtilting motor

LED Cal.
Devices

PL Obs.
Sub Unit
Sub-Unit

BBM
NP telescope
Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

AT : Along Track Direction
CT : Cross Track Direction

7

Infrared Scanning Radiometer
SGLI IRS
SGLI-IRSOBS Light

SWI DET
SWI-DET 45deg folding mirror rotates
continuously at 81rpm.
 Observation light throughRitchey Chretien type telescope
is divided with two wavelength
region.
9 Shortwave Infrared detector(SWI‐DET)
9 Thermal Infrared detector((TIR‐DET).
)
 SWI‐DET uses InGaAs typedetectors at ‐30deg C using
peltier cooler.
 TIR‐DET uses PV‐MCT typedetectors at 55K using
mechanical stirling cooler.
8

SCAN
MOTOR

OpticalBench

Sterling
CoolerBLACK
BODY

TIR-DETOperation Concept f the SGLI, SPIE Incheon, October 13, 2010

SGLI Operation Concept
GCOM
User Committee
missionrequirment

SGLI Operation
Concept study
groundd systemtrequirment

SGLI groundsystemdevelopment.

SGLI Operation Concept Study
1) Wide swath / Observation Frequency
2) Daytime & Night time Observation
3) Observation Resolution
Æ data volume
Æ downlink stations
Æ onboard recorder volume
3) VNR‐PL Tilting Operation
Æ AerosolAl scattering
i anglelÆ directional observation of land surface
Æ F/F Control for the disturbance4) Operational Load Simulation
Æ Station load
Æ Commanding loadÆ plannning & realtime operation
Æ data processing load
Æ Off nominal case operation5) ground system performance req.

Operation Concept f the SGLI, SPIE Incheon, October 13, 20109

Observation Frequency
 GCOM-C1 orbit is“34daysy repeatporbit”
with “3.8days quasi
repeat cycle”.
ALOS SCAN-SAR OBS（J（Jan.
28 2009）28,

ALOS AVNIR-2 OBS
70k
70km

1150kmÆ Average 2 days frequency
observation is possible for
middle latitude. (35deg N/S)

(Feb 24,(Feb.
24 2009）

SGLI-VNR 1,150km（MODIS Jan
Jan. 28
28, 2009）

SGLI-IRS
G
1,400km,1400km（MODIS Jan. 28, 2009）SGLI VNR 1day OBS Area
（GLI OBS Mar. 20, 2003）
2003）
Operation Concept f the SGLI, SPIE Incheon, October 13, 201010

Observation Scenario
VNR-PL OBS

VNR-NP OBS

FWDOBSSolar Light

DAY

NIGHT

BACK
OBS

IRS-SWI OBS

LAND

So
olar Light

Solaar Light

SW1,2,4 :
1km
SW3 :
250m

IRS-TIR OBS

1km OBS

LAND
1km
OBS

DAY

NIGHT

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

SW1,2,4 : 1km
SW3 : 250m

11

Observation Resolution
 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
Rule Æ
DAY
1km

NIGHT
250m

DAY
250m

NIGHT
1k
1km

250m Obsfor Day Mode
Land Area(21.0Mbps)

DAY
1km
1k

Operation Concept f the SGLI, SPIE Incheon, October 13, 201012

Onboard Recorder budget& Data Latency
 Output data rate from SGLI is two digits or more bigger than AMSR2 becauseof high resolution 250m observation over land.
 Downlink rate from GCOM-C1 is one digits or more bigger than GCOM-W1.
Æ Onboard recorder budget should be carefully studied and big impacts ondata latency.
latency
SGLI Output▽DAY-250m
20MbpsDAY SIDE

NIGHT SIDE

15Mbps
10Mbps
5Mbps▽DAY-1km▽DAY-1km▽NIGHT 250m

▽NIGHT-1km

0Mbps-10min

0min

10min

20min

30min

40min

50min

60min

70min

80min

90min

100min110minGCOM‐W1
10MspsAMSR2 87.4kbps⇒ 66Mbyte/rev

Recording
6.3Gbyte/rev
SVAL Station Pass

Playback @ 138Msps D/L
6.0Gbyte/pass

EL 10deg
EL 5deg

9 ‐ 10 min

EL 0deg-10min

0min

10min

20min

30min

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

40min

50min

60min

70min

80min

90min

100min110min120min13

Downlink station & Onboard Recorder
Observation Scenario and Resolution req.
250m for land and coastal observation,observation 1km for open ocean observation
Downlink Station• Svalbard downlink station
Æ good visibility (14 or 15 passes per day) for the polar orbit satellite.
Æ global observation data downlink.
• Japanese domestic station
Æ quasi real time transmission to Japanese domestic users
Æ backup of Svalbard station.
• Direct downlink capability to the user local station.
Onboard Recorder• The solid memory type recorderÆ totalt t l recorderd amountt ini orderd tot recordd andd
playback the global observation
data without lack of data.
Æ 72Gbytes (BOL) including memory degradation
effects for 5 years mission life
Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

Visiblility of
Svalbard
StationSvalbard
Station14

VNR-PL Tilting Operation• VNR-PL tilting function from +45deg (forward looking) to -45deg (backward
looking).
• Aerosol Scattering angle requirement from the retrieval algorithm
Æ the forward looking for northern hemisphere, the backward looking for thesouthern hemisphere.
• The additional looking angle requirement like a bidirectional observation of land
surface is under discussion for the planning activity.
Aerosol Mie Scattering
Forward Looking(+45deg)

Nadir Looking(0deg)

ExampleBackward Looking(-45deg)

180

scattering angle [deg]150

Solar Light
Backward
Looking120

Forward
Looking

Backk
B
Scattering

90

60

60deg

30

ForwardNadir
Backward

0
-90

SOUTH

-60

-30
0
30
solar lattitude at obs point [deg]60satellite orbit direction

Forward
Scattering

120degForward
Looking90

NORTH
satellite direction

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

Backward
Looking15

Operational load simulation
 Operational load simulation considering the operation concept
Æ The planning activity for satellite operation and ground data receiving andprocessing
i are definedd fi d Data processing & distribution requirement
Æ SGLI standard products and research products defined for both scene typeand global type products (sinusoidal tile products).
Æ The performance and interface specification to the other ground system.
Æ The convenience for the data handlingg and analysis
y at user side.
Pre-Launch
Operation
StudyLong Term
Operation
Coordination

3 months
observation
planning

Tracking
Stationplanning

GCOM C1
GCOM‐C1
Ground System
Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

Realtime
Operation

Data
processing& distribution

Product
Users

52 products req
req.
Standard

Research

Radiance(L1A/L1B)

2

‐

Land

9

5

Atmosphere
p

8

3

Ocean

7

7

Cryosphere

4

8

Total

30

22

16

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.
LED CAL

Solar
So
a C
CAL

LED and Monitor
Bench

Backward Tilting
PL telescopes

NP Tele.
Right

Tilt Mechanism
Deployed
Spectralon Diffuser

Diffuser Deploy
Mechanismwith safety function

PL telescope
Tilting Mechanism

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

NP Tele.
CenterNP Tele.
Left

NP Tele.
Right

NP Tele.
CenterTilt Mechanism

NP Tele.
Left

Sun

17

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

Earth Observation
SCAN
MIRROR+Z (Earth)

Diffused
S l Light
Solar
Li h

Dee Space
Deep
S a e

+X
(Sat Velocity) +Y(Sat.
(Space)Light Guide
SCAN
MIRROR

Light
Guide

ε > 0.98

BLACK
BODY

1.6micron LED& Halogen Lamp

BLACK
BODY

Operation Concept f the SGLI, SPIE Incheon, October 13, 201018

Onboard Calibration Device& Calibration
C lib ti M
ManouverÆ The calibration input from different geometric direction provides
us withith goodd informationi f
ti forf theth systematictti calibration
lib ti error.
Æ SGLI calibration uses both onboard calibration device andcalibration manouver.
1st

2nd

3rd

4th

5th

1st year
6th 7th

8th

9th 10th 11th 12th 1st

▽

Major
M
j
Milestone

Onboard
Calib atio
Calibration
Device2nd

2nd Year
3rd 4th

5th

5th Year
9th 10th 11th 12th

8th▽

Launch

▽

Ver 1
Ver.
1.0
0 Release
Routine Operation Phase

Initial CAL/VAL Phase
Initial On-Orbit Check Out

designed EOL
Routine Operation Phase

Weekly Sun Calibration (LED Calibration as B/UP)△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△△△△△ △△△△ △△△△ △△△△ △△△△

Black body Calibration△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△ △△△△△△△△ △△△△ △△△△ △△△△ △△△△

Lunar Calibration Manouver△

Calibration
Manouver

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

△

Sun Calibration Manouver for β correction△△(TBD)△(TBD)△(TBD)△(TBD)

Yaw 90deg Calibration Manouver△

Vical &
Cross
Calibration

Callibration Campaign

Operation Concept f the SGLI, SPIE Incheon, October 13, 201019

Calibration Manouver
Lunar Calibration Manouver
9 Moon reflecting solar light is a stable lightsource as a long term calibration referenceof the optical sensors.
9 Lunar calibration manouver is done atevery 29 days interval (= synodic periodof the moon and the sun)
9 SGLI observes same phase angle moon
(7deg) during 5 years mission for the
integral lunar calibration.

Sun Angle Correction Manouver
9 As earth rotates around the sun, solar
direction gradually change because of theelliptical and inclined orbit of the earth.
9 The local sun time tolerance is anotherfactor for this solar angle change.
change9 Solar angle calibration manouver is done
to establish the solar angle dependency
database for this calibration.
calibrationObs. Angle Correction Manouver
9 Because VNR uses wide FOV’s
pushbroom type CCD sensor, the satellite
observation angle dependency is anotherkeyy calibration factor.
9 The satellite yaw axis is 90deg rotated toobserve the almost same earth target withdifferent CCD detectors.
9 The homogeneous target is used for thiscalibration.

Operation Concept f the SGLI, SPIE Incheon, October 13, 201020

SGLI EM phase activity
 1st SGLI preliminary design review (PDR-1) was held on Dec. 22, 2009 2nd SGLI PDR ((PDR-2)) for CCD was held on March 23,, 2010.
 Based on these design review SGLI BBM refurbishment and Engineering
Model (EM) manufacturing is approved.
 Full EM test is planned including environmental test,
test such as Vibration,
Vibration
Shock and Thermal Vacuum Test.
【BBM Phase】
Scanning
Radiometer
Unit
(SRU)

Refurbish

Designn

Electronics
Unit
(ELU)

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

None

Manufacturing
Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

SRU TEST
including
Env. Test
I/F Test(SRU-ELU)(Satellite)

MechanicalParts... etc

ELU(EM)【【PFM Phase】】

FlightModel(PFM)

ELU TEST
including
Env. Test
Test▲
Summer 201121

GCOM-C1 Project Status GCOM-C1 satellite design is on going. Main design focus is on the difference
between GCOM-W1
GCOM W1 and GCOM-C1GCOM C1 satellite because of mission difference,difference suchas high data rate handling from SGLI.
 GCOM-C1 satellite system PDR is for July-October, 2010.
 The target launch of GCOM-C1GCOM C1 is JFY2014.
JFY2014
Japanese
Fiscal Year

JFY
2006

JFY
2007

JFY
2008

JFY
2009

JFY
2010

GCOM-W1 Project start

Milestone

GCOM-C1GCOM
C1GCOM-W1
LaunchGCOM-C1GCOM
C1 Project start

SDR

GCOM-W1

JFY
2011

Phase-A

PDR

Phase-B

Phase-CPh
Phase-AA

Operation Concept f the SGLI, SPIE Incheon, October 13, 2010

JFY
2013

JFY
2014

GCOM-C1
Launch(TBD)

CDR
Phase-D

SDR
P Ph
Pre-Phase-A
A

JFY
2012

PDR
Ph
Phase-B
B

Ph
Phase-CC

CDR
Ph
Phase-DD

22

Conclusion
 GCOM is JAXA’s GEOSS contribution of global observation for water
cycle,
y , radiation budget
g and carbon cycle.
y SGLI is the optical sensor on GCOM-C1 satellite.
 Bread Board Model (BBM) design and test activity has successfullycompleted.
 SGLI PDR is complete on March 23, 2010. Engineering Model (EM)manufacturing is under way.
 The EM testing including environmental test and I/F test with satellite
system is planned.
 The operation concept is under study for the input to the SGLI
supporting ground system design.

Operation Concept f the SGLI, SPIE Incheon, October 13, 201023

Back up slides

Operation Concept f the SGLI, SPIE Incheon, October 13, 201024

SGLI Standard Products (1 of 2)
Target accuracy*1

TOA radiance(including system geometriccorrection)

VNR,SWI
Land/coast: 250m,
offshore: 1km,
polarimetory:1km
Other VNR,SWI:
TIR
daytime (+special
Land/coast: 500m,
operation)
offshore: 1km

Radiometric 5%(absolute*3)*5
Geometric<1pixel

VNR,SWI: 5% (absolute*3),
1% (relative*4)
TIR: 0.5K (@300K)
Geometric<0.5pixel

VNR,SWI: 3% (absolute*3),
0.5% (relative*4)
TIR: 0.5K (@300K)
Geometric<0.3pixel

Precise geometric correction

both

250m

<1pixel*6<0.5pixel*6<0.25pixel*6

Atmospheric corrected reflectance((incl. cloud detection))

250m

0.3 (<=443nm),
0.2 ((>443nm)) (scene)() *7

0.1 (<=443nm),
0.05 ((>443nm)) (scene)() *7

0.05 (<=443nm),
0.025 ((>443nm)) (scene)()*7

Vegetation andd carbon
cycle

Land

Standard accuracy*1

Surfacereflectancce

CommonnRelease threshold*1

radiancee

Area group

Product

Vegetation index

250m

Grass:25%(scene),
forest:20%(scene)

Grass:20%(scene),
forest:15%(scene)

Grass:10%(scene),
forest:10%(scene)

Above‐ground biomass

Day/night

Grid size

TIR and land
2.2μm: both

Daytime

1km

Grass:50%, forest: 100%

Grass:30%, forest:50%

Grass:10%, forest:20%

1km

Grass&forest: 40% (scene)

Grass& forest:20% (scene)

Grass&forest:10% (scene)

Shadow index

250m 1km
250m,

Grass&forest: 30% (scene)

Grass& forest:20% (scene)

Grass&forest:10% (scene)

fAPAR

250m

Grass:50%, forest: 50%

Grass:30%, forest:20%

Grass:20%, forest:10%

Leaf area index

250m

Grass:50%, forest: 50%

Grass:30%, forest:30%

Grass:20%, forest:20%

500m<3.0K (scene)<2.5K (scene)<1.5K (scene)

Vegetation roughness index

temperaSurface temperature
ture

Both

Common note:*1: The “release threshold” is minimum levels for the first data release at one year from launch. The "standard" and "research" accuracies
correspond to full- and extra success criteria of the mission respectively. Accuracies are shown by RMSE basically.
Radiance data note:*2: TOA radiance is derived from sensor output with the sensor characteristics, and other products are physical parameters estimated using
algorithms including knowledge of physical, biological and optical processes*3: absolute error is defined as offset + noise*4: relative error is defined as relative errors among channels, FOV, and so on.
*5: Release threshold of radiance is defined as estimated errors from vicarious, onboard solar diffuser, and onboard blackbody calibration becauseof lack of long-term moon samples
Land data note:*6: Defined as RMSD from GCP*7: Defined with land reflectance~0.2, solar zenith<30deg, and flat surface. Release threshold is defined with AOT@500nm<0.25

Operation Concept f the SGLI, SPIE Incheon, October 13, 201025

SGLI Standard Products (2 of 2)
A
Area
G
Group

Atmosphere

Cloudaerosol

Ocean
color
Ocean

ProductP
d t
Cloud flag/Classification
Classified cloud fraction
Cloud top temp/height
Water cloud OT/effective radius
Ice cloud opticalp
thickness
Aerosol over the oceanLand aerosol by near ultra violet
Aerosol by Polarization
Normalized water leaving
radiance (incl. cloud detection)
Atmospheric correction param
Photosynthetically available
radiatioin

Day/nightD/ i ht Grid
G id size
i
Both
1km
DaytimeBothDaytime60% (443~565nm)

Daytime

Chlorophyll-a concentration
In-water

ReleaseRlthresholdth h ld*1
10% (with whole-sky camera)
20% (on solar irradiance)*81K*910%/30% (CloudOT/radius) *11
1km (scene),
30%*110 1deg (global)
0.1deg0.1(Monthly τa_670,865)*14
0.15(Monthly τa_380)*14
0.15(Monthlyτa_670,865)*14

80% (AOT@865nm)
250m (coast)
20% (10km/month)
1km (offshore)
4~9km (global)−60~+150% (offshore)−60~+150% (offshore)−60~+150%
60 150% ((offshore)
ff h )

Suspended solid concentration
C l d diColoreddissolved
l d organici mattertttemperaSea surface temperature
ture

Crryosphere

Snow and Ice covered area (incl.
Area/
distributi cloud detection)on
OKhotsk sea-ice distribution
Snow and ice surface
SurfaceTemperature
properties
Snow grain size of shallow layer

BothDaytimeStandardStd d accuracy*1
T
Targett accuracy*1
Incl. below cloud amount
Incl. below cloud amount
15%(on solar irradiance)*810%(on solar irradiance)*8*10
3K/2km (top temp/height)
1.5K/1km (temp/height)*10*13100% (as cloud liquid water ) 50%*12 / 20%*13
70%*13
20%*1314
0.1(scene τa_670,865)*0.05(scene τa_670,865)
0.15(scene τa_380)*14
0.1(scene τa_380 )0.15(scene τa_670,865)*14
0.1(scene τa_670,865)
50% (<600nm)
30% (<600nm)
0.5W/m2/str/um (>600nm)
0.25W/m2/str/um (>600nm)
50% (AOT@865nm)
30% (AOT@865nm)
15% (10km/month)−60~+150%−60~+150%−60~+150%
60 150%500m (coast)
1km (offshore) 0.8K (daytime)
0.8K (day&night time)
4~9km (global)
250m (scene)
10%(vicarious val with other 7%
1km (global)
sat data)
sat.
250m
10%
5%
500m (scene) 5K (vicarious val with other sat.
2K
1km (global) data and climatology)
250m (scene) 100%(vicarious val with50%
1km (global) climatology between temp-size)

10% (10km/month)−35~+50% (offshore),−50~+100% (coast)−50~+100%−50~+100%
50 100%0.6K (day&night time)
5%
3%
1K
30%

Atmosphere note:*8: Comparison with in‐situ observation on monthly 0.1‐degree*9: Vicarious val. on sea surface and comparison with objective analysis data
*10: Inter comparison with airplane remote sensing on water clouds of middle optical thickness*11: Release threshold is defined by vicarious val with other satellite data (e.g., global monthly statistics in the mid‐low latitudes)*12: Comparison with cloud liquid water by in‐situ
in situ microwave radiometer*13: Comparison with optical thickness by sky‐radiometer (the difference can be large due to time‐space inconsistence and large error of the ground measurements)*14: Estimated by experience of aerosol products by GLI and POLDER

Operation Concept f the SGLI, SPIE Incheon, October 13, 201026

SGLI Research Products (1 of 1)
Area GroupLand

Application

Product

Day/night

Grid size

Release threshold*1

Land net primary production

Daytime1km

30% (yearly)

Water stress trend

N/A

500m

10% *15 (error judgment rate)

Fire detection index

Both

500m

20% *16 (error judgment rate)250m

30% (error judgment rate)

1km

10%

Land cover typeLand surface albedo

Atmosphere

Cloud

Water cloud geometrical thickness

RadiationbudgetLong-wave radiation flux

O
Ocean
color
l

E h ti zone d
Euphotic
depththIn-water

Inherent optical properties

Daytime

300m
DaytimeShort-wave radiation flux

Downward 13W/m2, upward 10W/m2

500m (coast), 1km (offshore),
70% (monthly)
4~9km (global)

Ocean

DaytimePhytoplankton functional typeerror judgment rate of large/ small phytoplankton
dominance<20%;20%; or error judgment rate of the
250m (coast),(coast) 1km (offshore)(offshore), dominancedominant phytoplankton functional group <40%
4~9km (global)

Redtideerror judgment rate <20%

multi sensor merged ocean color
Area/
distribution
CryosphereeSurfacepropaties

Boundary

Downward 10W/m2, upward 15W/m2 (monthly)

250m (coast), 1km (offshore), 30%
4~9km (global)a(440): RMSE<0.25, bbp(550): RMSE<0.25

Ocean net primary productivity

Application

1km (scene), 0.1deg (global)

250m (coast), 1km (offshore)−35~+50% (offshore), −50~+100% (coast)multi sensor merged SST

Both

500m (coast), 1km (offshore)

0.8K (day&night time)

Snow and ice classification

N/A

1km

10%

Snow covered area in forest and mountain

250m

30%

Snow grain size of subsurface layer

1km

50%

250m( scene), 1km (global)

50%

1km

7%

Snow grain size of top layer

DaytimeSnow and ice albedo
S
Snow
impurityiit

250 ( scene),
250m(
) 1k
1km ((global)l b l)

50%

Ice sheet surface roughness

N/A

1km

0.05 (height/width)

Ice sheet boundary monitoring

N/A

250m

<500m

Research product note:*15: Evaluate in semiarid regions (steppe climate etc.)
etc )*16: Fires >1000K occupying >1/1000 on 1km pixel at night (using 2.2um of 1 km and thermal infrared channels)

Operation Concept f the SGLI, SPIE Incheon, October 13, 201027