R&D of JAXA Satellite Application Mission

Keizo Nakagawa Japan Aerospace Exploration Agency (JAXA)

Satellite Technology Innovation Office

Agenda

1. Earth Observation Mission A) ALOS-2 B) GCOM-C1 C) GPM/DPR D) EarthCARE/CPR E) GOSAT-2 F) JAXA-DLR Joint L-band SAR Mission ParaSAR G) Vegetation LiDAR (MOLI)

2. Engineering Experiment Mission A) SLATS B) SPAISE

3. Business Support Mission A) SmartBus Programme B) Onboard Computer with SpaceWire Network

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Agenda

1. Earth Observation Mission A) ALOS-2 B) GCOM-C1 C) GPM/DPR D) EarthCARE/CPR E) GOSAT-2 F) JAXA-DLR Joint L-band SAR Mission ParaSAR G) Vegetation LiDAR (MOLI)

2. Engineering Experiment Mission A) SLATS B) SPAISE

3. Business Support Mission A) SmartBus Programme B) Onboard Computer with SpaceWire Network

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ALOS-2 (1/2) • The Advanced Land Observing Satellite-2 “Daichi-2” (ALOS-2) is a follow-on mission of

the “Daichi” (ALOS).

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Sensor information: PALSAR-2 : Phased Array type L-band SAR Size: 3 m x 10 m Power: 6120 W (peak) / 3944 W (average) Swath: 25 km to 490 km Resolution: Along track : 3 m to 100 m Cross track: 1 m to 100 m

Satellite information Orbit: Sun-Synchronous, Descending local time

12:00 , Altitude = 628 km, Inclination = 97.9 deg.

Size:16.5 m ×3.7 m ×9.9 m Weight: 2120kg Power: 5140W Launch: 2014

X Y

Z

• ALOS-2 mission fulfills social needs. • Disaster monitoring of damage areas • Continuous updating of data archives related to

national land and infrastructure information • Effective monitoring of cropland • Global monitoring of tropical rain forests to identify

carbon sinks

ALOS-2 (2/2) • PALSAR-2

– Improvement of spatial resolution (PALSAR:10m → PALSAR-2 : 1 to 3 m ) – Improvement of observation frequency ( PALSAR:5days → PALSAR-2 : 1 to 2 days )

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70°

8° 350 km or 490 km

25 km x 25km

70°

50 or 70km

observable range 1160km

Spotlight mode 25 km x 25 km

8°

Additional observation mode

Satellite flight direction

Unobservable range 80km

spacial resolution : 1 to 3 m

・higher observable range ・Improvement of observation freqency

right-and-left looking function

GCOM-C1 (1/2)

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Satellite Information Orbit: Sun-synchronous, Descending local time 10:30AM,

Altitude = 798 km, Inclination = 98.6 deg. Size: 4.7m(L) x 16.5m(W) x 2.6m(H) on orbit Weight: Max. 2100kg Power: 4000W (EOL) Launch: JFY2016 Mission instrument:

Second-generation Global imager (SGLI) • VNR: Visible and Near-infrared Radiometer • IRS: Infrared Scanning Radiometer

Sensor Information

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SGLI Spec. VNR IRS

Scan type Push-broom electric scan Wisk-broom mechanical scan

Observation channels

Non-polarization

11ch

Polarization 2ch

Shortwave Infrared

4ch

Thermal Infrared

2ch

Polarization angle - 0 /60 /120

deg. - -

Tilt angle - +45 /- 45 deg. - -

IFOV 250 m 1 km 250 m / 1 km 500 m

Swath 1150 km 1150 km 1400 km 1400 km

Earth View Window

Sun Cal. Window

Deep Space Window

Solar Diffuser Non Polarized Observation Telescopes 24deg FOV (x3)

Polarized Observation Telescopes 55deg FOV (x2) SGLI VNR (ELU)

SGLI IRS (ELU)

Global Change Observation Mission 1st - Climate

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GCOM-C1 (2/2)

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Policy design through prediction improvement

Operational use for fishery, sea route, weather forecast, etc.

monitoring and understanding of the earth environment change

3°C

Air temperature prediction

Prediction results GCOM observation

• Improvement of parameterization about radiation budget and carbon cycle, etc. in climate prediction model.

• Verification and improvement of prediction of the earth environment change including the water cycle by comparison with the satellite observation.

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

Carbon cycle • Vegetation cover • Primary production • Coastal environment

• Surface temperature • Sea level • Snow and sea ice area • Environmental change • Rain/drought distribution

• Extreme weather frequency

• Land cover

Climate system model

Comparison

Input

Model prediction

Improve accuracy

Future prediction

Water cycle • Water vapor, cloud,

precipitation • Soil moisture • Sea ice, snow • SST, wind

Data application Knowledge

GCOM-C GCOM-W

GCOM observation

Frequent and long term (>10yer) global observation system

GCOM Mission Concept

atmosphere

land ocean

cryosphere

Improve the accuracy of both long-term and short-term weather forecasts

Improve water resource management in river control and irrigation systems for agriculture

Core Satellite (JAXA, NASA) Dual-frequency precipitation radar (DPR)

GPM Microwave Imager (GMI) • Precipitation with high precision • Discrimination between rain and snow • Adjustment of data from constellation

satellites (The core satellite will fly in non-sun-synchronous orbit.)

Constellation Satellites (International Partners)

Microwave radiometers Microwave sounders

• Global precipitation every 3 hours

• GPM: An international satellite mission to be launched by JAXA and NASA in 2014 for precipitation measurements worldwide

Core Satellite TRMM Era GPM Era

Constellation Satellites

2 satellites/3hr

8 satellites/3hr

GPM/DPR (1/2) Global Precipitation Measurement/ Dual-frequency Precipitation Radar

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3D-distribution of precipitation

2D-distribution of precipitation

Flight direction

GMI 407 km altitude, 65 deg inclination

5km

Range resolution = 250m and 500m

DPR

Dual-frequency precipitation radar (DPR) consists of -Ku-band (13.6GHz) radar : KuPR (similar to TRMM/PR) and -Ka-band (35.5GHz) radar : KaPR

KuPR (13.6GHz) Swath width = 245km

KaPR (35.5GHz) Swath width = 120km

Microwave radiometer Swath width = 800 km

GMI: GPM Microwave Imager

The DPR was developed by JAXA and NICT.

GPM/DPR (2/2)

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EarthCARE/CPR (1/2)

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Sensor Information CPR: W-band millimeter Doppler radar - First spaceborne millimeter Doppler radar - Largest reflector for W-band Earth observation satellite.

Specification

- Frequency: 94.050GHz - Beam width: 0.095deg. (~φ800m footprint) - Transmit power: >1.5kW @EOL - Pulse width: 3.3µs - Doppler measurement accuracy: 1.3m

Earth Clouds, Aerosols, Radiation Explorer(CARE)

Satellite Information Cooperative mission of ESA and JAXA - Orbit: Sun-Synchronous, Descending local time 14:00 ,

Altitude = 393 km, Inclination = 97.05 deg. - Mass: 2250kg - Power: 1625W - Launch: 2016

Sensors - CPR: Cloud Profiling Radar - ATLID: Atmospheric Backscatter LiDAR - MSI: Multi-Spectral Imager - BBR: Broadband Radiometer

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2.5m

240kg 316W

Cloud, Profiling, Radar(CPR)

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EarthCARE/CPR (2/2)

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S/C Flight direction

Vertical resolution: 500m

Observation height range 20km（low latitude） 16km 12km（high latitude）

S/C altitude : 400km

CPR

Foot print: Less than 800m

Sampling:100m

Transmitting power: more than 1.5kW@EOL

©NASA Example of CloudSat Observation

Horizontal resolution (Integration length):500m

• Earth CARE/CPR improves prediction accuracy of the global warming by clarification of radiation effect and interaction between clouds and aerosol, observing global 3-D structure of clouds and aerosol.

Items GOSAT-2 GOSAT Target Gases CO2，CH4，O3，H2O，CO CO2，CH4，O3，H2O Instruments ①Fourier Transform spectrometer

②Imager ①Fourier Transform spectrometer ②Imager

Local Time 13:00 +/- 0:15 13:00 +/- 0:15 Altitude 666 km 666 km Launch JFY2018(TBD) JFY2009

GOSAT-2 (1/2)

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TANSO-FTS specifications GOSAT-2 GOSAT FOV/number 10.5 kmf / 1 10.5 kmf / 1 Spectral Ranges (um)(cm-1)

①0.75-0.77 (12,950-13,250) ②1.56-1.69 (5,900-6,400) ③1.92-2.08 (4,800-5,200) ④2.33-2.38 (4,200-4,300) ⑤5.5-14.3 (700-1,800)

①0.75-0.77 (12,900-13,200) ②1.56-1.72 (5,800-6,400) ③1.92-2.08 (4,800-5,200) ④5.5-14.3 (700-1,800)

Observation Mesh 160km (5 points in the CT direction) 160km (5 points in the CT direction) Avoidance of the cloud Intelligent pointing ------- TANSO-CAI specifications GOSAT-2 GOSAT Spectral Ranges (nm) Forward Viewing

① 330-350 ② 420-440 ③ 860-880 ④ 1555-1645

Backward Viewing ⑤ 370-390 ⑥ 540-560 ⑦ 860-880 ⑧ 1555-1645

① 370-390 ② 664-684 ③ 860-880 ④ 1555-1645

Spatial Resolution/swath 500m/1,000km (except ④and⑧) 1km/500km (④and⑧)

Band 1-3: 500m/1,000km Band 4: 1500m/750km

Greenhouse gases Observing SATellite-2

Sensor Information

Satellite Information

GOSAT-2 (2/2)

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Contribution to policy making against climate changes

Decision about emission reduction targets based on scientific fact

Reduction of future forecast uncertainty concerning global warming.

Evaluation of emission reduction efforts and its effectiveness against global warming - Forest preservation - Extinction and

prevention action of peat fire

- REDD+ action

Monitoring emission of greenhouse gases

Detection of Earth climate system change on sub-continental scale

Evaluation of REDD+ actions

Monitoring of hot spots Monitoring of air pollution Monitoring of dynamic states

of particle matter and SLCP(short-lived climate pollutants)

- improvements of the atmospheric concentration measurement precision

- improvement of estimation accuracy of flux

- estimation of the anthropogenic emissions

- improvement of the natural emission estimation accuracy

- grasp of the flux of the large forest area in the developing countries

- Monitoring of the Hot spots

- Monitoring of the aerosols in the atmosphere

Mission Requirements Objectives of Observation

JAXA-DLR Joint L-band SAR Mission ParaSAR (1/2)

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Sensor ‒ L-band SAR (Synthetic Aperture Radar)

SAR Performance (Stripmap mode) ‒ Swath width: 350km (global observation within 8 days) ‒ Resolution: 3m

Candidate Orbit ‒ sun-synchronous (8 days revisit cycle) ‒ Altitude: 760 km

Innovative L-band radar mission for monitoring Earth dynamic processes with new techniques and technologies (under study)

Formation flying interferometry SAR

Digital beam forming with large deployable reflector (Tx: wide beam, Rx: narrow beam)

Solar array

Feed elements

Φ15m LDR

Mission Information

Digital beam forming and large deployable reflector for high imaging capacity

High frequency observation for disaster and environmental monitoring

Two satellites formation flying for high accuracy 3D imaging

Tx Rx

Each receiving element has narrow beam pattern

Feed elements

Ground

JAXA-DLR Joint L-band SAR Mission ParaSAR (2/2)

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L-band SAR is well suited to monitoring vegetation, disaster and land deformation

JERS-1(1992-1998) ALOS(2006-2011)

Pi-SAR-L(1998~2011) Pi-SAR-L2(2012~)

Observation with wider swath (higher obsevation frequency) and better resolution are required for next generation L-band SAR, ParaSAR

ALOS-2(JFY2013~)

Natural forest Natural mangrove forest Natural re-growth Acacia Oil Palm Rubber Coconut Open area Other Water

Polarimetric SAR for land use classification in Riau, Sumatra

(ALOS / PALSAR)

Quick and detailed monitoring of disaster area High accuracy imaging for Land use classification and carbon estimation (biomass) Earth deformation monitoring (earthquake, volcano, DEM) …

Long heritage of L-band SAR in Japan

Epicenter 2011/4/11 M7.0

Epicenter 2011/3/11 M7.0

★

★

-5.9 0 5.9cm

Interferometry SAR for Tohoku-Oki Earthquake

(ALOS / PALSAR)

Vegetation LiDAR (MOLI) (1/2)

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Candidate Orbit Altitude: 400 km, Inclination: 51.6 deg.

Observation Accuracy: 1 m (Object:Tree height on plan)

Required laser power and radius of mirror are below. - Laser power：< 100 mJ/pulse - Radius of mirror： 0.7 m

Conceptual Diagram (under study) Mission Information

Footprint…2x2 arrayed footprints (1064 nm only) - Using 2x2 arrayed detector to reduce the error of tree height due to sloped surface.

Sensors - Space-borne LiDAR

- Wavelength: 1064 nm and 532 nm - Pulse width: 5-7 ns (FWHM) - Pulse repetition frequency: 150Hz

- Imager - Resolution: 2 m - Swath: 500 m ~ ~ Example of waveform for a

footprint. From waveforms, useful information such as tree height will be available.

Transmitted pulse (divided into 4)

2×2 arrayed footprints

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Advantage of Mission The only spaceborne LiDAR designed to observe vegetation areas.

Vegetation LiDAR (MOLI) (2/2)

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ALOS-1/-2

GCOM-C1

MOLI

• 3D information is obtained which is important to biomass estimation and currently lacking.

Image information (including DSM )

or or

3D information (tree height)

・Land cover, vegetation index, biomass (accuracy is not sufficient) are estimated from 2D image data.

• For accurate estimation of above ground biomass, 3D information is essential. • Currently, only field surveys or airborne LiDAR data are available, but data quantity is not

sufficient. • Vegetation LiDAR (MOLI) lets us obtain much more 3D information of vegetation on global

areas, which drastically improves the estimation accuracy of the biomass.

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• 3D information obtained by MOLI and image data of other satellite will drastically improve the estimation accuracy of the biomass.

Agenda

1. Earth Observation Mission A) ALOS-2 B) GCOM-C1 C) GPM/DPR D) EarthCARE/CPR E) GOSAT-2 F) JAXA-DLR Joint L-band SAR Mission ParaSAR G) Vegetation LiDAR (MOLI)

2. Engineering Experiment Mission A) SLATS B) SPAISE

3. Business Support Mission A) SmartBus Programme B) Onboard Computer with SpaceWire Network

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Objectives of Super Low Altitude Satellite Much lower altitude: about 200km Orbit keeping by ion engine thrust Quality earth observation by relatively small sensor High spatial resolution for passive sensor Low consumption power for active sensor such as SAR and LIDAR

“SLATS” is engineering test satellite before operational one Verification of super low altitude satellite system, measurement of atmospheric density

in super low altitude and monitoring on-orbit data about atomic oxygen.

Satellite Information Orbit Mission: 250-180km Circular

Size (on-orbit) 2.5m(X)×5.2m(Y)×0.9m(Z)

Mass about 400kg

Mission life more than 1.5 year (dependent on injection orbit)

Mission sensor

(1) AO Monitoring System (a) QCM Sensor and Controller (b) Material Degradation Monitor (Optical Camera) (2) Optical Sensor for imaging the earth

Launch JFY2016

Overview of Super Low Altitude Test Satellite (SLATS)

SLATS(Super Low Altitude Test Satellite) (1/2)

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Ion engine technology

Apply

- Small-sized - Low cost - High resolution

- Small-sized - Wide-band radar - High resolution

- Observation of 2D wind direction and velocity

(first in the world)

SLATS(Super Low Altitude Test Satellite) (2/2)

Super Low Altitude Remote Senging Satellite

SLATS (Super Low Altitude

Test Satellite)

Wind observation using Doppler LIDAR

High resolution SAR

High resolution optical imaging

- Orbit keeping technology using ion engine system

- Acquisition of atmospheric data

- Verification of remote sensing technology

On-orbit Verification

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SPAISE2 (SPace based AIS Experiment 2) (1/2)

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Orbit (Mounted on ALOS-2)

Mission Information

Main Sensor : Cross Dipole Antenna received frequency: AIS#1(161.975MHz)&AIS#2(162.025MHz) or AIS#3(156.775MHz)&AIS#4(156.825MHz)

*AIS#3&#4 are new channel for satellite AIS

minimum receiver sensitivity: -112dBm sampling rate: 76.8kHz

size: 1050mm×800mm×800mm weight: 7kg×2

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Ground Station

Experiment Partner

JAXA

ALOS-2

Japan Coast Guard

SPAISE2

AIS signal (ship’s position, speed, type, destination etc.)

AIS: Automatic Identification System

SPAISE2 (SPace based AIS Experiment 2) (2/2)

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▲ ship (60m～) detected by SAR ● ship (～60m) detected by SAR ＋ ship detected by AＩＳ shore station ○ match ○ roughly match (error in position or ship size)

SPAISE2 (2013～ )

・Receiver sensitivity is improved from SPAISE and can get more AIS signals. ・Receive new satellite AIS channels (#3,#4). ・Matching AIS&SAR first in the world.

Sample of AIS&SAR matching

SPAISE (2012/5～ ) on SDS-4

・Successfully received AIS signals on orbit. ・Monitoring arctic passage. etc.

AIS data plot of 1 week

EEZ AIS shore station covered area

• AIS shore station can NOT cover maritime navigation of sea beyond 50km from shore

*EEZ is much wider than AIS shore station cover area.

Agenda

1. Earth Observation Mission A) ALOS-2 B) GCOM-C1 C) GPM/DPR D) EarthCARE/CPR E) GOSAT-2 F) JAXA-DLR Joint L-band SAR Mission ParaSAR G) Vegetation LiDAR (MOLI)

2. Engineering Experiment Mission A) SLATS B) SPAISE

3. Business Support Mission A) SmartBus Programme B) Onboard Computer with SpaceWire Network

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SmartBus Programme

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Inmarsat XL

0

5

10

15

20

25

0 1 2 3 4 5 6 7打上質量 (ｔ)

発生電力

(kW

)

Boeing 702 (米国）

SS/L LS1300 (米国）

Lockheed A2100 ( 米国）

OSC STAR2/2.4 (米国）

Astrium Eurostar E3000 ( 欧州)Thales Spacebu4000 ( 欧州）

CAST DFH-4 (中国）

JSC-ISS Express1000N ( ロシア）

NPO Lavochkin Navigator (ロシア）

Khrunichev Yakhta (ロシア)ISRO I-3K (インド）

NEC (日本)MELCO (日本）

国内限界性能2.5kW/t

傾きが低いほど、性能が悪い

国産衛星10kW / 5t

欧州新型バス12kW / 6.6t

Inmarsat XL

DirecTV -12

Sky terra1

Intelsat -22Intelsat 21

Thuraya -1

MEXSAT1

EchoStar XI

Hispasat 1E

EchoStar XVII

SIRIUS FM -5 EchoStar XIV

EchoStar XV

Telstar 14R

XM -5

SES -4

Intelsat 19

BSAT -3b

BSAT -3c

Vinasat -2

JCSAT -13

Vinasat -1

JCSAT -12

AMC 21

NSS -9

OptusD3

Intelsat16HYLAS -2

Intelsat15

SES1

COMS

Arabsat 5A

YahSat 1B

KA -SAT

Astra -2F

Astra 3B

HOT BIRD 9

Amazonas 2

Atlantic Bird -7

Astra 1M

HOT BIRD 10

Apstar 7

RASCOM -QAF1R

Chinasat 9

Eutelsat W3C

Nilesat 201

Turksat 3A

Eutelsat 10AChinasat -1A

Simon Bolivar

Luch -5A Electro L

Express -MD2

GSAT8 GSAT10

WINDS

DRTS

ETS-VIII

Superbird7

ST-2

EchostarG1

米国新型バス20kW / 6t

JAXA新型バス

(US) (US)

(US) (US)

(EU) (EU)

(China) (Russia)

(Russia)

(Russia) (India)

(Japan) (Japan)

US’s New bus 20kW/6t

Current capability : 2.5kW/t

Weight At Launch (t)

Elec

tric

Pow

er (k

W)

Japan’s current bus. 10kW/5t

Europe’s new satellite bus. 12kW/6.6t

With JAXA’s technical support, this development program will strengthen Japan’s industrial competitiveness by achieving light-weight and high-power SmartBus System.

Commercialization after 2020. 2 – 3 sales (10% of market) per year.

Market prediction in communications satellites ■Large satellites will account for 40% of market

Goal : 4(kW/t)

JAXA New bus

Onboard Computer with SpaceWire Network (1/2)

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Software - ACFS: Attitude Control Flight Software - DHFS: Data Handling Flight Software - TCFS: Thermal Control Flight Software - BCFS: Battery Control Flight Software - FDIR: Failure Detection Isolation and Recovery - Middleware / RTOS / Firmware

Conceptual Diagram Main Specification

Hardware - 64bit radhard MPU - 1 of 2 Standby redundancy with SpW network - Mission interruption time < 3sec - I/F : SpaceWire, RS-422

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■Onboard computer with SpaceWire Network for next-generation satellite systems ・Functional integration (Data-handling, Attitude Control and Thermal /Battery Control) ・Full SpaceWire network architecture ・Adaptability for various mission requirement ・Improvement of software reusability ・Standby redundancy with SpaceWire network

2013/10/24

Onboard Computer with SpaceWire Network (2/2)

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Previous satellite (GCOM) Onboard computer with SpaceWire Network

Mass Total 34.4 kg 15 kg Size Total 3547 cm2 1280 cm2

Integration of standard components: Down sizing and weight saving.

Thank you for your attention!