Japan Resources Observation System and Space Utilization Organization

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1

About JAROSAbout JAROSJAROS was established on 21st November, 1986 by Toshiba

Corporation, NEC Corporation, Hitachi, Ltd., Fujitsu, Ltd. andMitsubishi Electric Corporation with the approval of the PrimeMinister and the Minister of International Trade and Industry toconduct R & D of a resources observation system to be loadedon the JERS-1 satellite.

Subsequently, R & D of a greenhouse gas observation systemwas added to the business of JAROS in December, 1989 forthe purpose of researching the state of the world-widedistribution of greenhouse gases.

In April 2006 JAROS has merged with JSUP(Japan SpaceUtilization Promotion Center). JSUP had extensively supportedthe space utilization projects of the government and privatesectors since established on 22 February 1986 with theapproval of the Prime Minister and the Minister of InternationalTrade and Industry.

The purpose of JAROS is to develop the earthresource observation systems, the green housegas measurement systems and the spaceuti l ization systems to secure the naturalresources, protect natural environment and utilizemicrogravity application.

Through our business JAROS contributes to theadvancement of science and technology in Japan,the growth of Japanese economy and thepromotion of international cooperation.

JAROS,s business activities are based on the

commissions from the Ministry of Economy, Tradeand Industry and Ministry of Education, Culture,Sports, Science and Technology.

Establishment of JAROS Purpose of JAROS

JAROS History

1986

1989

1987

1993

1996

1997

1999

2006

R & D of Resources Observation System for JERS-1 (1986 to 1999)Development of OPS (Optical Sensor) and SAR (Synthetic Aperture Radar) for the JERS-1 (Japanese Earth Resources Satellite-1)

R & D of Resources Observation System for NASA TERRA Satellite (1987 to the present)R & D of the ASTER (Advanced Space borne Thermal Emission and Reflection Radiometer) for NASA's Terra Satellite

R & D of Environmental Monitoring System for ADEOS Satellite (1989 to 1997)R & D of the IMG (Interferometric Monitor for Greenhouse Gases) for the ADEOS (Advanced Earth Observation Satellite)

Advanced Study on Environmental Monitoring (1993 - 1996)Research on the IMG-II (Interferometric Monitor for Greenhouse Gases-II)

R & D of Next Generation SAR for ALOS Satellite (1993 to the present)R & D of the PALSAR (Phased Array Type L-Band Synthetic Aperture Radar) for the ALOS (Advanced Land Observation Satellite)

Merged with the Japan Space Utilization Promotion Center (JSUP) (April. 2006)

Established (1986)

Hitachi, Ltd.Fujitsu, Ltd.Mitsubishi Electric CorporationNEC CorporationJapan Petroleum Exploration Co., Ltd.JGI, Inc.Earth Remote Sensing Data Analysis CenterRemote Sensing Technology Center of JAPANJapan Aerospace Exploration AgencyJapan Oil, Gas and Metals National CorporationFujikin, Inc.IHI Aerospace Co., Ltd.Mitsubishi Heavy Industries, Ltd.

(as of April, 2007)

Cooperative OrganizationOrganization

Board of Councilors

Board of Directors Auditors

Chairman Advisors

Executive Managing Director

Managing Director

Secretariat

General Affairs Department

Technical Department

Space Utilization Department

R & D Department

Steering Committee

*表1と4本文欧文/2007 07.3.30 4:15 PM ページ 1

Remote SensingRemote Sensing

2

Space Remote Sensing

Space remote sensing is a technology to observe the earth from

space using onboard observation equipment.

The most popularly used sensors today are;

1. Optical sensors which detect visible rays and infrared rays, etc.

reflected or radiated from land, surface of oceans, air and other

objects.

2. Radio sensors which, like radars, irradiate radio waves to

objects to measure the reflected waves.

Following the growth of industries, many problems have emerged,

such as the indiscriminate exploitation of resources, including

tropical rain forests, climate change due to an increase of CO2 in

the air, depletion of the ozone layer and air pollution. It is now

imperative to conduct the domestic as well as global surveillance

and observation of the global environment in terms of resources,

vegetation, air and oceans, etc. Accordingly, the importance of

space borne remote sensing capable of continually observing the

entire earth is ever increasing. R & D activities on various sensors

for resource detection, geological and land use surveys and the

observation of vegetation, air, oceans and the environment and

mapping are in progress in many countries along with R & D of

data analysis and processing technologies.

Space remote sensing R & D activities are in progress on various

sensors in many countries for resource detection, the observation

of vegetation, air, oceans and other purposes together with the

development of data analysis and processing technologies.

Sensors are classified as passive sensors which detect rays and

radio waves from objects and active sensors which irradiate radio

waves or lights to objects to measure the reflected radio waves or

lights.

●Images by JERS-1: Izu Peninsula

●SARDetailed data on land can be obtained day or night regardless of the presence of

cloud cover. (Observation date: February 3, 1998)

●Optical Sensor (OPS visible and near infrared radiometer)Detailed data on land can be obtained during the day using reflected sunlight.

(Observation date : January 11, 1997)

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3

Remote SensingRemote Sensing

Optical Sensors (Sounder Type)

Sounder type optical sensors used for spaceborne remote sensingmeasure temperature, atmospheric pressure and trace gases inthe atmosphere, etc. Basically, these sensors measure thespectrum of rays radiated, reflected or absorbed by substances byvarious means.

The right figure explains the Michelson-Fourier spectrometer whichis used for the IMG developed by JAROS.

The principle of this spectroscopy is to measure the patterns ofinterference of an incident ray, called an interferogram, caused bythe movement of a moving mirror in an optical system consisting ofa fixed mirror, moving mirror, beam splitter (half mirror) anddetector. The inverse Fourier transformation of this interferogramproduces the spectrum (frequency-amplitude characteristics) of theincident ray. The spectral data are then processed to the verticaldistribution of concentration and the temperature of variousgreenhouse effect gases and others.

FocusingInterference occurs

Transmission of Reflected Beam BReflection ofReflected Beam A

FixedMirror

MovingMirror Moving

Detector

Interferogram

A（0.5Ⅰ0）

B（0.5Ⅰ0） ReflectedBeam B

Incident Ray（Ⅰ0） ReflectedBeam A

Transmission of Reflected Beam A and Reflection of Reflected Beam B

Beam Splitter(50% transmission, 50% reflection)

●Principle of Michelson-Fourier Spectroscopy

Optical Sensors (Imager Type)

Imager type optical sensors observe reflected light and infraredlight from the earth and generate image data. These types ofsensors are most widely used in space.

Many spaceborne optical sensors separately observe "visible andnear infrared", "short-wave infrared" and "thermal infrared" regionsrespectively. Each region is divided into several spectral bandsand the sensor obtains image data of all bands simultaneously.The discernibility of ground objects i.e. spatial and spectralresolution, is an important element of these sensors andpanchromatic sensors and visible/near infrared sensors with a highresolution are being used.

The constituents of land (soil, rocks, vegetation, lakes and rivers,etc.), oceans, snow and ice have inherent wavelengthcharacteristics in reflection, absorption and radiation. Thereforeanalyses of the spectral patterns for each band can discriminatethe types of rocks and other minerals, and can also discriminatevegetation type and ocean pollution, etc. Imager type opticalsensors are the most popularly used for resource surveillance.

Altitude information on topographical features and three-dimensional images can also be synthesized from two data sets

which are obtained by two imagers.

Further R & D activities on imaging sensor technologies arecurrently in progress to improve the spatial and spectral resolution.

.45

0.40 0.50 0.60 0.70 0.80 13.5

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LANDSAT-4,5（TM）（US）

LANDSAT-6,7（ETM）（US）

SPOT-4（HRVIR）（France）

SPOT-5（HRG）（France）

JERS-1（OPS）（Japan）

IMG（FT-IR）（Japan）

ASTER （Japan）

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（STEREO）

Visual Rays

Wavelength（µm）

Infrared Rays

L BAND SAR

Panchromatic

Panchromatic

Panchromatic.79 .89 1.58 1.75

Cosmic Rays/Gamma Rays/X-Rays Microwave/Ultra Short-Wave - Short-Wave/Medium-Wave/Long-WaveInfrared RaysUltravioletRays

●Wave Regions of Typical Optical Sensors

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4

Synthetic Aperture Radar (SAR)

SAR is one of sensors for space remote sensing. It is a kind ofimaging radar which is capable of producing high resolutionimages with a relatively small antenna by collecting data at shortintervals along the path of a satellite and then conducting thesynthetic processing of the large amount of data. SAR has theadvantage of being capable of observation regardless of theweather or time of day because it uses microwaves. The favoritefield of SAR is the extraction of topographical features. The SAR isvery effective in getting on the geological structure, types of rocksand vegetation from the analysis of the collected data. It is used asa sensor for resource survey, monitor of disaster and environment,acquisition of topography and mapping.

Compared with optical sensors, the higher penetration ability ofmicrowaves allows the SAR to gather useful information under

clouds, vegetation or sandy land. It is now expected that theinformation which cannot be obtained by a single SAR can beobtained through a combination with information obtained byoptical sensors.

Interferometry makes it possible to get topographical maps andsurface deformation maps associated with crustal movement.

Wide-ranging R & D activities to improve the SAR’s performanceand functions are currently in progress to develop an advancedSAR with a higher resolution, less ambiguity (ghost) and multi-functions. The operation of a constellation system consisting ofseveral satellites is being considered at present for the purpose ofimproving the observation frequency.

●Topographical Changes of Okushiri Island Due to Earthquake

This image was developed by the interferometric data obtained

by the SAR onboard the JERS-1 before and after an

earthquake and shows the topographical changes caused by

the earthquake.

(Hokkaido southwest offshore earthquake in July, 1993)

11.8 cm indicates a single cycle of

interference fringes and corresponds to half

of the wave length (λ). Interference fringes

indicate changing values of the height.

(Data supplied by METI/JAXA; image prepared by ERSDAC)

11.8 cm

0 cm

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5

ProjectProject

●

●

●JERS-1 Characteristics

Resources Observation Systems for JERS-1 (OPS, SAR)

The JERS-1 (Fuyo-1) is a satellite which can cover almost all ofthe land of earth and is utilized not only for the survey of mineralresources but also for environment, disaster and coastalmonitoring.

This satellite was jointly developed by JAROS which wasresponsible for the development of the resources observationsystem and by NASDA which was responsible for thedevelopment of the satellite system. It was launched onFebruary 11, 1992 from the Tanegashima Space Center usingan H-I rocket.

The resources observation system consists of an imager typeoptical sensor (OPS), a synthetic aperture radar (SAR), amission data recorder (MDR) and a mission data transmitter(MDT).

The OPS is composed of a visible and near infrared radiometer(VNIR) and a short-wave infrared radiometer (SWIR) andconducts observation in seven bands from visible to short-waveinfrared. While both Bands 3 and 4 of VNIR observe the visibleinfrared rays of the same wavelength band, the different FOVs(field of view), i.e. forward and nadir, enable that 3D images canbe obtained by synthesizing both data.

Unfortunately, observation by the SWIR ceased in December,1993 because of malfunction of the cooling system. Observationof the visible and near infrared region and observation by theSAR continued to function beyond the designed life time(February, 1994) until operation stop of the satellite itself(October, 1998). JERS-1 transmitted a huge volume of data forsix years and eight months.

●Main Characteristics

●JERS-1 (Fuyo)

Visible and Near Infrared Radiometer (VNIR)

Spectral Range

Swath Width

Spatial Resolution

Power Consumption

Mass

0.52 - 0.86 µm (four bands)

75 km

18.3 m x 24.2 m

196 W

32 kg

Short-Wave Infrared Radiometer (SWIR)

Spectral Range

Swath Width

Spatial Resolution

Power Consumption

Mass

1.60 - 2.40 µm (four bands)

75 km

30 m x 30 m

392 W

60 kg

Synthetic Aperture Radar (SAR)

Center Frequency

Bandwidth

Polarization

Swath Width

Transmitter Peak Power

Spatial Resolution

Power Consumption

Mass

Dimensions

Mass

Power

Orbit

1,275 MHz (L Band)

15 MHz

H-H

75 km

1.3 kW

18 m x 18 m

769 W

228 kg

approx. 1 m x 1.8 m x 3.4 m

approx. 8 m x 3.4 m

approx. 1,340 kg

Altitude

Inclination

Period

Recurrent Period

SolarPaddle

Sun-synchronous sub-recurrent orbit

2,053 W

approx. 570 km

98°

90 minutes

44 days

Body

The left panel is the SAR antenna and the right panel is the solar paddle

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Resources Observation System for Polar Orbit Platform (ASTER)

The ASTER (Advanced Spaceborne Thermal Emission and ReflectionRadiometer) is the successor to OPS which was mounted on theJERS-1 and has improved functions and performance. It is mountedon the TERRA satellite developed under the international earthobservation program proposed by NASA (National Aeronautics andSpace Administration).

Development of the ASTER commenced in 1987 and the fullyoperational unit was handed over to NASA in March, 1997. Followingintegration of the TERRA and system testing, it was launched at10:57:39 on December 18, 1999 (local time) from the Vandenberg AirForce Base using an ATLAS IIAS rocket.

The ASTER is composed of a visible and near infrared radiometer(VNIR), a short-wave infrared radiometer (SWIR) and a thermalinfrared radiometer (TIR). The TIR was not seen in the systemonboard the JERS-1. The greatly improved functions andperformances include improved spatial and radiometric resolution, anincreased number of observation bands, expansion of the observationrange to the thermal infrared region, introduction of pointing functionsand use of highly reliable cooling systems.

Band 3 of the VNIR has two separate observation systems withdifferent FOVs, i.e. nadir and backward, to produce 3D images.Although the design life of five years was reached on 17th December,2004, the ASTER is still pursuing its mission, hoping to last for anotherthree years.

●Main Characteristics

●TERRA Chracterristics

Visible and Near Infrared Radiometer (VNIR)

Spectral Range

Swath Width

Spatial Resolution

Power Consumption

Mass

0.52 - 0.86 µm (three bands)

60 km

15 m x 15 m

93 W

79 kg

Short-Wave Infrared Radiometer (SWIR)

Spectral Range

Swath Width

Spatial Resolution

Power Consumption

Mass

1.600 - 2.430 µm (six bands)

60 km

30 m x 30 m

167 W

126 kg

Thermal Infrared Radiometer (TIR)

Spectral Range

Swath Width

Spatial Resolution

Power Consumption

Mass

8.125 - 11.65 µm (five bands)

60 km

90 m x 90 m

246 W

150 kg

Dimensions

Mass

Power

Orbit

approx. H 6.8 m x 3.2 m (when stowed)

approx. 9.1 m x 5.0 m

approx. 5,035 kg

Altitude

Inclination

Period

Recurrent Period

Solar Paddle

Sun-synchronous sub-recurrent orbit

2,530 W

approx. 705 km

98.2°

98.9 minutes

16 days

Body

Thermal Infrared Radiometer

Short Wave Infrared Radiometer

Common Signal Processer

Main Power System

Visible Near Infrared Radiometer(Electronics)

Visible Near Infrared Radiometer(Optics)

7

Images (ASTER)

●Example of Forest Fire Observation Using Shortwave Infrared Data

●3D Image Using Visible/Near Infrared Data(Mt. Yatsugadake)

●Heat Islands of Tokyo Using Thermal Infrared Radiometer Data

Forest fire in the San Bernadino Mountains, 80 km east of Los Angeles

Smoke from a forest fire The red area indicates burned-out forests

Visible/near infrared image

Visible/near infrared + shortwave infrared image (courtesy of NASA/GSFC)

10th August, 2002 Daytime 10:34 Ground surface temperature

16th July, 2002 Night 21:43 Ground surface temperature

The high temperature areas were extended using shortwave infrared data.

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●ADEOS Characteristics

Interferometric Monitor for Greenhouse Gases (IMG)

The development of IMG (Interferometric Monitor for GreenhouseGases) commenced in 1989 to observe the concentration anddistribution of CO

2and other greenhouse gases in the atmosphere

which were believed to be a cause of global warming, a growingmajor global environmental issue. The IMG is a sounder typeoptical sensor and employs a Michelson-Fourier transformspectrometer which is suitable for the specified observationpurpose. It was loaded onboard the ADEOS (Advanced EarthObserving Satellite: Midori) and was launched on August 17, 1996from the Tanegashima Space Center using an H-II rocket.

Following the initial check-out, normal operation commenced onNovember 26, 1996. However, it became inoperational because ofan accidental rupture of the solar paddle of the satellite on June 30,

1997. The valuable data obtained by the IMG during its activeobservation period of some eight months were made available toresearchers as they were the world's first greenhouse effect gasesobservation data using a Fourier transform spectrometer fromspace.

Meanwhile, further research aimed at developing the nextgeneration IMG was conducted from FY 1993 till FY 1996. Thisresearch focused on technologies of important elements relating tothe sensor system, mechanism of the moving mirror, detectorelements and cooler, etc. to increase the observation density andto shorten the observation time.

●IMG

0 50 100 150 200 250

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100

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●Methane Concentration Seven and a Half Months After Start of IMG Observation (Altitude: 1,000 hPa)

The above is the result of inputting the gas concentration obtained by IMG observation to a four-dimensional assimilation model which takes the advection and dispersion by air movement intoconsideration.The concentration is high in the northern hemisphere, especially around the North Pole.

●Main Characteristics

(The side panel is opened.)

Spectral Range

Spectral Resolution

Absolute Accuracy

Stability of Measurements

Instantaneous Field of View (IFOV)

Mass

Power Consumption

Dimensions

Interferogram Scan Time

714 - 3,030 cm-1 (three bands)

0.1 cm-1

1 K or less

0.1 K or less

8 km x 8 km (each band)

133 kg

149 W

approx. 1.2 m x 0.9 m x 0.7 m

10 seconds

Dimensions

Mass

Power

Orbit

approx. 4 m x 4 m x 5 m

approx. 3 m x 26 m

approx. 3,500 kg

Altitude

Inclination

Period

Recurrent Period

Solar Paddle

Body

Sun-synchronous sub-recurrent orbit

4.5 kW

approx. 800 km

98.6°

101 minutes

41 days

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Phased Array Type L-Band Synthetic Aperture Radar (PALSAR)

The concept study started in 1993 for the next generation SAR asthe successor of JERS-1 SAR. In1995 it was decided by the SpaceActivity Committee that the new SAR was jointly developed byJAROS and JAXA under the name of Phased Array Type L-BandSynthetic Aperture Radar (PALSAR) onboard Advanced LandObservation Satellite (ALOS). JAROS was responsible for allelectric equipments of PALSAR and JAXA for overall systems.

PALSAR operates in L-band, same as JERS-1 SAR, but has much

more advanced characteristics. Key feature is the adoption ofActive phased array antenna. It provides various operation modessuch as high resolution mode, wide swath mode ( scan SARmode) and full polarization mode. PALSAR has the down-link viadata relay satellite.

The PALSAR was launched from Tanegashima Space Center onJanuary 24, 2006, and has been operational from October 2006after initial check-out, calibration and validation phase.

●ALOS Characteristics

●ALOS

PALSAR

DRC ANTENNA

SOLAR PADDLE

●Main Characteristics (Courtesy of JAXA)

Dimensions

Mass

Power

Orbit

approx. 3.6 m x 4 m x 6.2 m

approx. 3.1 m x 22.2 m

approx. 4,000 kg

Altitude

Inclination

Period

Recurrent Period

SolarPaddle

Body

Sun-synchronous sub-recurrent orbit

7 kW or more (EOL)

approx. 700 km

98.2°

99 minutes

46 days

Main Observation Mode High Resolution Mode Wide Swath Mode Polarimetry Mode

1.27 GHz (L-Band)

2.0 kW

680 kg/1.28 kW

28 MHz

HH or VV, HH + HV or VV + VH HH or HV HH + HV + VV + VH

10 m

2 Looks

70 km

8 - 60°

-21 dB

100 m

3 - 5 Swaths

250 - 350 km

18 - 43°

-23 dB

30 m

30 km

8 - 30°

-28 dB

Center Frequency

Bandwidth

Polarization

Spatial Resolution

Number of Looks etc.

Swath Width

Incident AngleNoise Equivalent to Back-scattering Coefficient

Transmitted Peak Power

Mass/Power Consumption

10

Images (PALSAR)

(Courtesy of METI and JAXA)The first image, taken at 22:16, February 15, 2006

Shimizu-City in Shizuoka PrefectureAbe River in black at left, Nihondaira Plane in center, Port Shimizu and Miho Peninsula at right.

Birds-eye view of Mt. Fuji and Izu PeninsulaPALSAR data taken at the off-nadir of 41.5 degrees is merged with the digital nationalland information provided by the Geographical Survey Institute.

The summit of Mt. Fuji (enlarged)

Satellite flight path

Direction of radioirradiation

METI, JAXA

METI, JAXA

VisionVision

11

Vision for Future Sensors

The Landsat satellite series which began with the Earth ResourcesTechnology Satellite (ERTS lanched in July, 1972, later renamedLANDSAT-1) launched by NASA has demonstrated the effectivenessand the wide application of spaceborne earth observation, opening anew horizon for remote sensing technology.

Remote sensing technology, which contributes to observation anddetection of various objects on the earth from space, has been steadilyadvancing with the development of satellite technologies, and isincreasingly playing an important role.

The ever increasing demand for improved observation functions andperformances formerly led to large satellites with various sensors.However, the effectiveness of single function, small satellites with alower development burden has been rediscovered, leading to thelaunch of commercial remote sensing satellites in recent years.

From the technological point of view, the development policy for opticalsensors is an improvement of the capability of identifying an objectthrough enhanced resolution, the use of multiple band and an improvedS/N ratio.

In the case of a synthetic aperture radar, the required improvement ofthe identification capability is sought through higher resolution, multipleband, multi-polarization and multi-beam. At the same time,interferometric technology will certainly advance.

From the viewpoint of observation systems, the introduction of pointingfunctions will improve the observation frequency of specific observationareas. Furthermore, the selection of an observation wavelength anddynamic range appropriate for a specific target observation will enablethe acquisition of the dimed data. Meanwhile, onboard processing suchas the selection and compression of data will be required to reduce theburden on the satellite system such as data recording andtransmission system.

On the ground, more advanced data processing (image processingand feature extraction, etc.), data storage and distribution functions willbe required to ensure a timely response to the ever expanding anddiversifying user needs.

Although there is a demand for ultimate high resolution and a multipleband function, it is believed that the demand for the sensors currentlyused for the LANDSAT and SPOT series, which are the main players intoday's remote sensing, will continue to provide appropriate data forusers who require the data continuity.

The dreams of further technological progress are endless, including atelescopic satellite which conducts constant monitoring with aresolution of 3 m from a geostationary orbit and a texture meter whichcan observe the ground texture with a resolution of several cm to 1 mfrom a low earth orbit.

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Space UtilizationSpace Utilization

Space utilization is to use physical properties in the micro-gravityenvironment.JAROS provides comprehensive support for the space utilization

projects of the government and private sectors to contribute theadvancement of science and technology and the development ofindustries in Japan.

12

JAROS promotes researches, investigations, experiments anddevelopments on various space utilization themes. JAROSencourages the use of the various means of micro-gravityexperiments, including drop tower, airplane, small rocket,Space shuttle and “Kibo” the Japanese Experimental Module(JEM) on the International Space Station.

JAROS widely gathers the scientific and technical information of space utilization fromdomestic and foreign publications and media and compiles the trends and prospects of spaceutilization into reports. JAROS distributes the reports to the relevant parties and makes thempublic on its home page.

JAROS organizes various symposiums,lectures and workshops to disseminates andenlighten the potentials and prospects of spaceutilization.

JEM "Kibo" on the international space station (courtesy of JAXA)

Research and Development

Dissemination and enlightenment

Compilation and Distribution of Information Symposium on space utilization

*表1と4本文欧文/2007 07.3.30 4:15 PM ページ 12

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Takara-cho

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Shinkansen

Sotobori St.

Tokyo

Chuoh St.

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Suzuran St.Heisei St.

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JAROS

Showa St.Subway Asakusa Line

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Japan Resources Observation System and Space Utilization OrganizationNichibei Building 2F24–2, Hatchobori 2-chomeChuo-ku, Tokyo, Japan 104-0032Tel: 03-5543-1061 Fax: 03-5543-1067Home Page URL: http://www.jaros.or.jp/

2007.4

25 m from the A4 Exit of Tokyo Metro Hatchobori Station

170 m from the B1 Exit of JR Keiyo Line Hatchobori Station

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