GCOM status

Keiji Imaoka

Earth Observation Research Center

Japan Aerospace Exploration Agency

AMSR-E Science Team Meeting

July 2008

Telluride, CO

2

Instrument Advanced Microwave Scanning Radiometer-2

OrbitSun Synchronous orbit　 Altitude： 700km, Inclination: 98.2 deg.

Size 5.1m (X) * 17.5m (Y) * 3.4m (Z)

Mass 1910kg

Power 4050W @ EOL

Launch JFY2011

Design Life 5-years

Status Phase-C

GCOM-W1 (Water)

GCOM 1st generation

GCOM-C1 (Climate)

Instrument Second-generation Global Imager

OrbitSun Synchronous orbit　 Altitude ： 798km, Inclination: 98.6 deg.

Size 4.6m (X) * 16.3m (Y) * 2.8m (Z)

Mass 1950kg

Power 4250W @ EOL

Launch JFY2013 (TBD)

Design Life 5-years

Status Phase-B

3

GCOM Status

Satellite systemGCOM-W1

Development of satellite: Phase-C

Development of AMSR2: Phase-C to D (under review)

GCOM-C1Now in Phase-B, waiting for phase-up review

Ground segmentGCOM-W1:Completed SDR and preparing for RFP

1 2 3 4 5 6 7 8 9 10 11 12 1 2 3 4 5 6 7 8 9 10 11 12 1 2 3 4 5 6 7 8 9 10 11 12 1 2 3 4 5 6 7 8 9 10 11 12 1 2 3

▲ ▲ ▲PDR CDR PSR

▲CDR

Phase-C Phase-D

GCOM-W1

AMSR2

2012

Phase-B Phase-C Phase-D Phase-E

▲launch

2008 2009 2010 2011

4

GCOM Status

ScienceGCOM 1st Research Announcement

Issued: Jan. 2008. Proposal due: Apr. 2008.

Selection of PI has already finished.

Cooperation between US-Japan is under discussion.

Workshop is currently scheduled in Jan. 2009.

FutureGCOM 2nd RA for GCOM-C1 is scheduled to be issued in this JFY, but will depend on project and budget condition.

Discussions began for GCOM-W2.

5

AMSR2 Instrument

AMSR2 Channel Set

Center Freq.[GHz]

Band width [MHz]

Polarization

Beam width [deg](Ground res.

[km])

Sampling interval

[km]

6.925/7.3

350

VandH

1.8 (35 x 62)

10

1.7 (34 x 58)

10.65 100 1.2 (24 x 42)

18.7 200 0.65 (14 x 22)

23.8 400 0.75 (15 x 26)

36.5 1000 0.35 (7 x 12)

89.0 3000 0.15 (3 x 5) 5

GCOM-W1/AMSR2 characteristics

Local time 13:30 LTAN

Swath width 1450km

Antenna 2.0m offset parabola

Incidence angle Nominal 55 degree

Deployed Stowed

Control Unit

Sensor Unit

Channels in 7.3GHz band for possible RFI mitigation.Two MWAs in control unit and mission module for redundancy.Improvement of HTS (warm load).

6

HTS design changes

Improvement of HTSChange of heat control methodology

Thermal Control Panel (TCP).Controlling heat of TCP and HTS case structure.

Blocking of thermal coupling between HTS and its outside.Change of temperature monitoring (e.g., number of points, vertical distribution).No change for absorbing material itself.

Temp. monitorHeater

AMSR sensor unit

Rotation center

Absorption material

Cutout for feed horns

Surface: MLI

AMSR2 sensor unit

Rotation center

TCP

Heat supply from HTS wall heaters

Heat supply from TCP

Heat control of AMSR/HTS Heat control of AMSR2/HTS

7

SGLI Instrument

SGLI channels

5000.23403000.712.0T25000.23403000.710.8T1

1000211(TBD)201.9502210SW4250575032001640SW3

10001501038201380SW2100050024857201050SW110002503003020865P210002502502520670P12502003003020865VN1125040030820865VN10

1000400350408763VN92502502102520670VN8250400622310670VN7250400903320565VN62502503504120530VN52504001205310490VN42503004006410443VN32504002507510412VN22502502106010380VN1

mVN, P, SW: -

T: NET

VN, P: W/m2/sr/m

T: Kelvin

VN, P, SW: nmT: m

IFOVSNR at LstdLmaxLstd

CH

SGLI channels

5000.23403000.712.0T25000.23403000.710.8T1

1000211(TBD)201.9502210SW4250575032001640SW3

10001501038201380SW2100050024857201050SW110002503003020865P210002502502520670P12502003003020865VN1125040030820865VN10

1000400350408763VN92502502102520670VN8250400622310670VN7250400903320565VN62502503504120530VN52504001205310490VN42503004006410443VN32504002507510412VN22502502106010380VN1

mVN, P, SW: -

T: NET

VN, P: W/m2/sr/m

T: Kelvin

VN, P, SW: nmT: m

IFOVSNR at LstdLmaxLstd

CH

• The SGLI features are finer spatial resolution (250m (VNI) and 500m (T)) and polarization/along-track slant view channels (P), which will improve land, coastal, and aerosol observations.

VN: Solar diffuser, Internal lamp (PD), Lunar by pitch maneuvers, and dark current by masked pixels and nighttime obs.

SW: Solar diffuser, Internal lamp, Lunar, and dark current by deep space window

T: Black body and dark current by deep space windowAll: Electric calibration

On-board calibration

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

Orbit (TBD)

Jan. 2013 (HII-A)Launch Date

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

1150km cross track (VNR: VN & P)1400km cross track (IRS: SW & T)

Scan width

GCOM-C SGLI characteristics (baseline of GCOM-C1 BBM design)

Nadir for VN, SW and T, +45 deg and -45 deg for P

Along track direction

3 polarization angles for PPolarization12bitDigitalization

Push-broom electric scan (VNR: VN & P)Wisk-broom mechanical scan (IRS: SW & T)

Scan

VN: Solar diffuser, Internal lamp (PD), Lunar by pitch maneuvers, and dark current by masked pixels and nighttime obs.

SW: Solar diffuser, Internal lamp, Lunar, and dark current by deep space window

T: Black body and dark current by deep space windowAll: Electric calibration

On-board calibration

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

Orbit (TBD)

Jan. 2013 (HII-A)Launch Date

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

1150km cross track (VNR: VN & P)1400km cross track (IRS: SW & T)

Scan width

GCOM-C SGLI characteristics (baseline of GCOM-C1 BBM design)

Nadir for VN, SW and T, +45 deg and -45 deg for P

Along track direction

3 polarization angles for PPolarization12bitDigitalization

Push-broom electric scan (VNR: VN & P)Wisk-broom mechanical scan (IRS: SW & T)

Scan

Visible & Near infrared push-broom Radiometer (VNR)

Polarization (along-track slant) radiometer (P)

Shortwave & thermal InfraRed (T) Scanner (IRS)

SGLI : Second generation GLobalImager

Visible & Near infrared push-broom Radiometer (VNR)

Polarization (along-track slant) radiometer (P)

Shortwave & thermal InfraRed (T) Scanner (IRS)

SGLI : Second generation GLobalImager

Multi-angle obs. for 670nm and 865nm

8

GCOM data flow

J AXA ground network

Researchers, practical fields, etc

Svalbard Domestic

Station

CMD(S-band),

HK-TLM(S-band),

R&RR(S-band)

CMD(S-band),

HK-TLM(S-band)

Observation data

(Global／X-band),

HK-TLM(X-band)

Observation data

(Around J apan／X-band)

Products

Tsukuba Space Center

Satellite condition monitoring

Operation planning Observation data processing

HK-TLM

(S-band)

CMD

(S-band)

HK-TLM

(S-band)

CMD

(S-band)

Observation data

(Global／X-band),

HK-TLM(X-band)

Observation data

(Around J apan／X-band)