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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
2013/10/24 MEWS26 2
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
2013/10/24 MEWS26 3
ALOS-2 (1/2) • The Advanced Land Observing Satellite-2 “Daichi-2” (ALOS-2) is a follow-on mission of
the “Daichi” (ALOS).
2013/10/24 MEWS26 4
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 )
2013/10/24 MEWS26 5
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)
6
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
MEWS26
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
2013/10/24
GCOM-C1 (2/2)
7 2013/10/24 MEWS26
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
2013/10/24 MEWS26 8
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)
2013/10/24 MEWS26 9
EarthCARE/CPR (1/2)
10
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
MEWS26
2.5m
240kg 316W
Cloud, Profiling, Radar(CPR)
2013/10/24
EarthCARE/CPR (2/2)
11 2013/10/24 MEWS26
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)
2013/10/24 MEWS26 12
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)
2013/10/24 MEWS26 13
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)
2013/10/24 MEWS26 15
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)
16
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
2013/10/24 MEWS26
Advantage of Mission The only spaceborne LiDAR designed to observe vegetation areas.
Vegetation LiDAR (MOLI) (2/2)
17
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.
2013/10/24 MEWS26
• 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
2013/10/24 MEWS26 18
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)
2013/10/24 MEWS26 19
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
2013/10/24 MEWS26 20
SPAISE2 (SPace based AIS Experiment 2) (1/2)
21 2013/10/24 MEWS26
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 are new channel for satellite AIS
minimum receiver sensitivity: -112dBm sampling rate: 76.8kHz
size: 1050mm×800mm×800mm weight: 7kg×2
21
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)
22 2013/10/24 MEWS26
▲ 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
2013/10/24 MEWS26 23
SmartBus Programme
2013/10/24 MEWS26 24
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)
25
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
MEWS26
■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)
2013/10/24 MEWS26 26
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!