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MITSUBISHI ELECTRIC CORPORATION PROPRIETARY INFORMATION ANY AND ALL UNAUTHORIZED REPRODUCTION OR DISCLOSURE STRICTLY PROHIBITED

IGARSS2011

Development of High Temperature Noise Development of High Temperature Noise Source (HTS) for Advanced Microwave Source (HTS) for Advanced Microwave

Scanning Radiometer 2 (AMSR2)Scanning Radiometer 2 (AMSR2)

July 28, 2011

Kamakura Works, Mitsubishi Electric Corporation

Tatsuhiro NOGUCHIGCOM-W1

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Contents

1. Introduction (GCOM)

2. AMSR2 Summary

3. HTS Design Concept

4. Evaluation

5. Conclusion

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GCOM: Global Change Observation Mission


GCOM-W1

Launch

GCOM-C1

Launch

GCOM-W2

GCOM-C2

GCOM-W3

GCOM-C3

GCOM-W1: AMSR2 (Advanced Microwave Scanning Radiometer 2)GCOM-C1 : SGLI (Second-generation Global Imager)

Sensor

Japanese fiscal year 2011 year

(W: Water, C: Climate)5-years

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GCOM： Global Change Observation MissionAMSR2： Advanced Microwave Scanning Radiometer 2

AMSR2 on GCOM-W1

AMSR2 SU (Sensor Unit)

GCOM-W1

+Y Axisperpendicular direction

to orbit plane

+Z Axisgeocentric direction

+X Axistraveling direction

・ Integrated Water Vapor・ Integrated Cloud Liquid Water・ Precipitation・ Sea Surface Temperature・ Soil Moisture, etc

Observation Data

・ Understand global environment changes Climate prediction models International environmental strategy・ Improve people’s lives Weather forecasting Fishery Information

ContributionAMSR2 CU (Control Unit)

5


AMSR2 CUAMSR2 SU

AMSR2 MWA

2. AMSR2 Summary

6


Key Parameters of Heritage AMSRSensor

Satellite

Antenna

Freq.GH（ｚ）

BWMH（ｚ） Pol CH Freq.

GH（ｚ）BWMH（ｚ） Pol CH Freq.

GH（ｚ）BWMH（ｚ） Pol CH Freq.

GH（ｚ）BWMH（ｚ） Pol CH

- - - - 6.975 350 VH 2 6.925 350 VH 2 6.9257.3 350 VH 4

- - - - 10.65 100 VH 2 10.65 100 VH 2 10.65 100 VH 2

- - - - 18.7 200 VH 2 18.7 200 VH 2 18.7 200 VH 2

23.8 400 V 1 23.8 400 VH 2 23.8 400 VH 2 23.8 400 VH 2

31.4 500 H 1 36.5 1000 VH 2 36.5 1000 VH 2 36.5 1000 VH 2

- - - - 50.352.8

160380 V 2 - - - - - - - -

- - - - 89-A89-B 3000 VH 4 89-A

89-B 3000 VH 4 89-A89-B 3000 VH 4

AMSR2AMSRMSR AMSR-E

0.5m Antenna (Fixed) 2m Antenna (Fixed) 1.6m Antenna (Deployable) 2m Antenna (Deployable)

MOS-1 (launch:1987)MOS-1b (launch:1990) ADEOS-II (launch:2002) Aqua (launch:2002) GCOM-W1

(scheduled for launch:2011)

6 frequency band, 14 ch 6 frequency band, 16 ch

KeyPara-meters

2 frequency band, 2ch 7 frequency band, 16 ch

2. AMSR2 Summary

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AMSR2 SU

HTS (High Temperature noise Source)

CSM (Cold Sky Mirror)

Feed

Main Reflector

Radiationfrom Earth

2. AMSR2 Summary

1,450km wide scanCalibrate once per each scan (1.5s), using HTS and CSM

Features

1,450km wide scan

1450km

55° 55°

61°

47.5°

AMSR2 observation concept

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SL

TL

Low temp.calibration point

TOBS

SOBS

　 Observationpoint

Brightnesstemperature

Microwavestrength

Calibration MethodCSM

FeedTCP (Thermal Control Panel)

HTS

Uniform temperature of microwave absorbersIrradiate Feed with stabilized brightness temperature

HTS Mission

300

HTS

unit： mmMicrowaveAbsorbers

300

300

(mass:4kg)

SH

TH

High temp.calibration point

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HTS Performance Specification

- Reference temperature of HTS : 20degC- Temperature distribution of Microwave Absorbers : 2.5degC or less


T : 2.5degC or less

20degC

HTS

Thermal Design Concepts

- Radiate a constant temperature heat to the microwave absorbers- Insulate microwave absorbers from the external thermal environment

Extremely sever specification

<Comparative example : a normal satellite equipment >

Allowed temperature range : -10 to +50degC

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Heater

Thermal Design (Heater Control)

・ Heater Control of HTS Walls and TCP・ Thermal Radiation from HTS Walls and TCP

Design Concept

Sensor Unit

Radiation heat from TCP

Radiation heatfrom HTS walls

MLI

To supportstructure

*Materials: Aluminum alloy (HTS wall / TCP)*Heater control: All six planes (HTS wall / TCP)


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Thermal Design (Thermal Insulation)MLI

•Solar heat power incidence•Outer space radiation heat

・MLI (Multi Layer Insulation)・ TCP and Sun-Shields for HTS・ Thermal insulation spacers

Design Concept Thermalinsulation spacers

Thermalinterface

Thermalinsulation spacers

Shield

Sensor Unit

Shield


12


4. Evaluation

(1) On-orbit Thermal Analysis

Analysis

AMSR2 Thermal Math Model

(2) IR Method(3) Solar Method

Thermal Vacuum Test

Thermal vacuum test configurations

IR method Solar method

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ItemsHigh temp.

caseLow temp.

case

Orbit

Altitude 699.6km

Inclination 98.186deg

Beta angle 32deg 13deg

Albedo 0.25 0.35

IR 258W/m2 216W/m2

Solar 1421W/m2 1289W/m2

Thermal optical properties EOL BOL

Controltemperature

HTS walls 20degC

TCP 20degC

Interfaceconditions

HTS 27degC 1degC

TCP 34degC -5degC

Feed 0degC 0degC

Thermal Analysis Condition

4. Evaluation

< 2.5degC< 2.5degCSpec.

139.8W91.1WTCP

Avg. power

8.0W2.9WHTS

avg. power

2.0degC1.8degCTemp.

distribution

High temp. case

Low temp. case

Case

Thermal Analysis Result

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17

18

19

20

21

22

23

0 1000 2000 3000 4000 5000 6000Time s

Tem

pera

ture

deg

C

Microwave absorbers’ temperature trends (high temperature case)

Sunshine SunsetSunset

Temperature fluctuation of feed coversIncidence of solar light from gap between HTS and TCP

Factor of temperature changes of microwave absorbers

4. Evaluation

1560s

1.8degC

3900s

1.5degC

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17

18

19

20

21

22

23

0 1000 2000 3000 4000 5000 6000Time s

Tem

pera

ture

deg

C

Microwave absorbers’ temperature trends

1.8degC < 2.5degC



1560s

4. Evaluation

Sunset SunsetSunshine

1560s

18.27 20.13

Temperature contour figure

(high temperature case)

Feed cover

Feed cover

[Unit:degC]

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17

18

19

20

21

22

23

0 1000 2000 3000 4000 5000 6000Time s

Tem

pera

ture

deg

C

Microwave absorbers’ temperature trends

1.5degC < 2.5degC



3900s

4. Evaluation

[Unit:degC]

Temperature contour figure

(high temperature case)

3900s20.02 21. 57 Sensor Unit

Solar light incidence

Sunset SunsetSunshine

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Temperature Distribution of Microwave Absorbers

・ Case1 Temperature Distribution ： 0.6 degC → Complete Validity verification of design concepts ・ Case2 Temperature Distribution ： 1.2 degC → Meet performance specification

Conclusion （ Thermal Vacuum Test IR Method）

9.649.68

9.659.55

9.74/9.63/9.19

9.52

9.77

9.009.55

9.70

9.34/9.95/10.1

9.29

9.84/9.89/9.37

9.639.479.05

9.64

9.59

9.57

9.729.05/9.69/9.92

9.74 10.1

10.0/9.97 9.34

9.989.97

9.70

9.76

10.210.1

9.899.88

9.88

10.010.09.29

10.1

9.26

[Unit:degC]Case 2

9.9510.0

9.949.89

9.93/9.93/9.75

9.89

9.99

9.749.90

10.0

9.82/10.1/10.2

9.82

9.94/10.0/9.66

9.879.949.70

9.96

9.95

9.90

10.09.74/9.97/10.0

10.0 10.2

10.0/10.0 9.78

10.110.1

10.0

10.0

10.310.1

9.999.99

10.0

10.010.19.83

10.23

9.67

[Unit:degC]Case 1

4. Evaluation

Items Case 1 Case 2

HTS Walls

10 degC

10 degC

TCP 10 degC

10 degC

Feed Dummy

10 degC

-19 degC

Rotation Yes Yes

Heater Panels

-85 degC

-85 degC

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-0.2

0.0

0.2

0.4

0.6

0.8

1.0

-50 0 50 100 150 200Time s

Tem

pera

ture

deg

C

-400

0

400

800

1200

1600

2000

Sol

ar l

ight

int

ensi

ty W

/m 2

Temperature Trends of Microwave Absorbers

0.3 degC << 2.5 degC

・ Temperature increase of microwave absorbers within Solar light incidence (150s)　　 0.3 degC max → negligible in orbit operation

Conclusion（ Thermal Vacuum Test Solar Method）

4. Evaluation

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･ Validity verification of the thermal design concepts of HTS was conducted by thermal analysis on orbit and thermal vacuum tests of development model

･ Specification of temperature distribution : 2.5degC or less

Design result: 1.8degC at high temperature case

2.0degC at low temperature case

･ Calibration and measurement performance of AMSR2 will be improved more than a previous model.

Conclusion

5. Conclusion

･ Launch within Japanese fiscal year 2011･ On-orbit evaluation

Future plan

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FIN

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AMSR2 Block Diagram

SENS UNIT (SU) CONT UNIT (CU)

DC/DCRX1-BDC/DC

RX1-A

CONTROL UNIT (CU)SENSOR UNIT (SU)

LNA-VLNA-H

LNA-VLNA-H

RX-VRX-H

RX-VRX-H

SPS

MWA-A

ADE-BADE-A

SPC-BSPC-A

Structure Structure

Integration PartsIntegration PartsRelease Bolt CatcherRelease Bolt Catcher

CSM

HTS

CAL ASSY

Deployment Structure

Antenna

Main Reflector

衛星ｼｽﾃﾑ

6.9GHz7.3GHz

10.65GHz

36.5GHz

89GHz-A

89GHz-B

18.7GHz23.8GHz

Feed

Separation Device Separation Device

EED

OBM-XV OBM-XH OBM-YHOBM+YV

TCS

Heater

TCC

Heater

10/18/23/89-A

DC/DCRX2-B

DC/DCRX2-A

6/36/89-B

GCOM-W1Satellite

Cable

MDC dataPCD dataTLMCMD

RX-VRX-H

RX-VRX-H

RX-VRX-H

RX-VRX-H

RX-VRX-H

Receiver

PDUC 1

ADM

PDUS

RX-VRX-H

MWA-B

PDUC 2 BUS

BUS

LNA-VLNA-H

LNA-VLNA-H

LNA-VLNA-H

RX-VRX-H

RX-VRX-H

SPS

MWA-A

ADE-BADE-A

SPC-BSPC-A

Structure Structure

Integration PartsIntegration PartsRelease Bolt CatcherRelease Bolt Catcher

CSM

HTS

CAL ASSY

Deployment Structure

Antenna

Main Reflector

衛星ｼｽﾃﾑ

10.65GHz

36.5GHz

89GHz-A

89GHz-B

18.7GHz23.8GHz

Feed

Separation Device Separation Device

EED

OBM-XV OBM+XH OBM-YHOBM+YV

TCS

Heater

TCC

Heater

DC/DCRX2-B

DC/DCRX2-A

6/36/89-B

GCOM-W1Satellite

BUS

Cable

MDP dataTime dataTLMCMD

RX-VRX-H

RX-VRX-H

RX-VRX-H

RX-VRX-H

LNA-VLNA-H

Receiver

PDUC 1

ADM

PDUSDC/DCRX2-B

DC/DCRX1-A

Thermal Control Panel

DIV

Back-up Chart

22


Item

Observation Frequency (GHz) 6.925 7.3 10.65 18.7 23.8 36.5 89 (A) 89 (B)

Band Width (MHz) 350 350 100 200 400 1000 3000 3000

Polarization

Temperature Resolution (K) 0.34 0.43 0.7 0.7 0.6 0.7 1.2 1.2

Dynamic Range (K)

Off-Nadia Angle deg（）

Swath Width (km)

Scan Period (sec)

Beam Width (deg) 1.8 1.8 1.2 0.65 0.75 0.35 0.15 0.15

IFOV [Az x El] (km) 35 x 61 35 x 61 24 x 41 13 x 22 15 x 26 7 x 12 3 x 5 3 x 5

Beam Efficiency (%) >90 >90 >90 >90 >90 >90 >90 >90

Sampling Interval (km) 510

Performance

V/H

2.7 340～

47.5

1450

1.5±1% (40rpm）

Key Performance of AMSR2

Back-up Chart

23


Back-up Chart

NEDT Comparison for AMSR-E/AMSR2

0

0.2

0.4

0.6

0.8

1

1.2

1.4

H V H V H V H V H V H V H V H V

6.9G 6.9G 7.3G 7.3G 10G 10G 18G 18G 23G 23G 36G 36G 89GA 89GA 89GB 89GB

ΔT[K

]

AMSR-E PFM Measured Data AMSR-E On-Orbit Data AMSR2 PFM Measured Data

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