IMAGE GALLERY
 
 
   PROGRAMS
  • Space Missions

  •  
  • RazakSAT

  • RazakSAT was jointly developed by SI and ATSB of Malaysia as an international collaborative program from 2001 to 2005. The mission was initiated by Malaysia to launch a medium-high resolution remote sensing satellite into Near Equatorial Orbit (NEqO). Due to its geographical location, Malaysia can have large benefits from NEqO satellite operation. From the baseline circular orbit of 685 km altitude with 9 degrees of inclination, the neighboring regions around Malaysian territory as well as other equatorial environment can be frequently monitored with unique revisit characteristic.


    LAUNCH
     

    RazakSAT was launched by Falcon 1 on
    14 July 2009 (UTC). [Courtesy of SpaceX]
    RazakSAT, having been ready for launch since August 2005, was launched into space on 14th of July, 2009. Due to its unique orbit requirement, Falcon 1 of SpaceX was selected as the launch vehicle considering its technical capacity and financial adequateness. Kwajalein site is the most suitable to obtain unique 9 degrees of inclination.


    EARLY OPERATION

    The ground station in Malaysia had the first contact within 80 minutes after the launch. The ground station at the latitude of 3.1 degrees allows communication link in every orbit, which is distinguished feature from polar orbiting satellites. The frequent contact opportunities enabled the initial attitude stabilization operation in a very short period. Initial de-tumbling and attitude control hardware check-up could be finished within a couple of hours. Three-axis stabilization and solar array deployment were achieved within 24 hours after the launch.


    SATELLITE

    RazakSAT is based on SpaceEye-2 design (SI-200 platform and EOS-C electro-optical payload). The satellite generates high quality Earth images of 2.5 m ground resolution in panchromatic band and 5 m in multispectral bands.

     

     



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  • DubaiSat-1

  • DubaiSat-1 is launched by Dnepr on 29 July
    2009 (UTC). [Courtesy of ISC Kosmotras]
    SI and EIAST of UAE started DubaiSat-1 project as an international collaborative program since 2006. DubaiSat-1 is an Earth observation small satellite that can generate 2.5 m resolution images. The satellite orbit was selected to have a sun synchronous characteristic. The global coverage nature of the orbit allows us to access various areas around the globe. DubaiSat-1 was developed within 2 years and ready for launch in 2008.


    LAUNCH

    DubaiSat-1 was launched into 680 km altitude sun-synchronous polar orbit from the Baikonuir launch site in Kazakhstan on 29th of July, 2009. Six satellites were launched in cluster by the Dnepr launch vehicle.

    First image of DubaiSat-1 - Palm Jebel Ali
    on 6 Aug 2009. [Courtesy of EIAST]

    EARLY OPERATION
    The conventional sun-synchronous orbit allows 2~3 ground contacts during daytime and 2~3 during nighttime. The initial operation of DubaiSat-1 was conducted smoothly, and the first image, Palm Jebel Ali of Dubai, was taken one week after launch.

     

    SATELLITE

    DubaiSat-1 is based on SpaceEye-2 design adopting SI-200 platform and EOS-C electro-optical payload. The satellite generates high quality Earth images of 2.5 m ground resolution in panchromatic band and 5 m in multispectral bands.

     



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  • X-SAT

  • X-SAT is a microsatellite technology demonstration mission of Centre for Research in Satellite Technologies (CREST), a joint laboratory of NTU and DSO of Singapore. The satellite weighs 105 kg at a size of 600 mm x 600 mm x 850 mm and carries a 10 m resolution multispectral (three spectral bands in the visible and near infrared spectrum) instrument as a primary payload. It was successfully launched on April 20th, 2011 by PSLV of ISRO.


    SI PARTICIPATION
    SI was contracted by DSO to provide a star sensor and the primary payload of X-SAT, called IRIS, with consultancy on X-SAT systems engineering and specific subsystem designs. SI delivered FM of star sensor and EQM and FM of IRIS.

     

    IRIS PAYLOAD

    IRIS payload is a push-broom type camera based on EOS-A with 10 m GSD for three multi-spectral bands. The swath width of the generated image is wider than 50 km. 8 Gbits of solid-state recorder is implemented as mass image storage. The access to the image data is through a 50 Mbits LVDS link that reads the encoded data from the storage after image acquisition and an 81 Mbits link that enables real-time access during imaging. The mass of the payload is less than 12 kg and the peak power consumption with all heaters on is less than 30 W.


        
     IRIS EQM Optics                                IRIS EQM Electronics

    PERFORMANCE SUMMARY OF IRIS PAYLOAD

        Parameter

    Feature

    Remarks

        Mass

    < 12 kg

    Optics < 5.0 kg, Electronics < 8.0 kg 

        Spectral Bands

    3 Multi-spectral Bands

    RG + NIR

        Resolution

    MS: 10 m (@ 685 km)

    SSO

        Swath-width

    > 50 km (@ 685 km)

     

        Physical Dimension

    Optics: 200 x 200 x 550 mm

     

    Electronics: 320 x 210 x 150 mm

     

     



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  • RASAT

  • RASAT is a microsatellite imaging mission of TUBITAK-UZAY, Turkey. The satellite weighs 113 kg at a size 700 x 700 x 554 mm and carries an Optical Imaging System (OIS) with a resolution of 7.5 m for panchromatic and 15 m for multispectral imaging as a primary payload. RASAT was sent up via the Dnepr launch vehicle of Russia on August 17th, 2011.

     

    SI PARTICIPATION

    SI was contracted by TUBITAK-UZAY to develop the primary payload of RASAT, called OIS, spacecraft dynamic environment simulator and attitude determination and control components such as star sensor, sun sensor and magnetometer.

     

    OIS PAYLOAD
    OIS payload is a push-broom type camera based on EOS-A with 7.5 m GSD for panchromatic and 15 m GSD for three multi-spectral bands in visible and near infrared spectrum. The swath width of the generated image is wider than 30 km. 7 Gbits of solid-state recorder is implemented as mass image storage. Mass of the payload is less than 6.5 kg and peak power consumption with all heaters on is less than 22 W.


        
       FM Optics                                                 FM Electronics


    PERFORMANCE SUMMARY of OIS PAYLOAD

        Parameter

    Feature

    Remarks

        Mass

    < 6.5 kg

    Optics < 3.6 kg, Electronics < 2.9 kg

        Spectral Bands

    PAN + 3 Multi-spectral Bands

    PAN + RGB

        Resolution

    PAN: 7.5m, MS: 15m (@ 700 km)

    SSO

        Swath-width

    30 km (@ 700 km)

     

        Physical Dimension

    Optics: 170 x 170 x 420 mm

     

        

    Electronics: 200 x 265 x 85 mm

     

     

     



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  • INTERNATIONAL PROGRAM EOS-C SYSTEM VERSION 3.0

  • This is a small satellite imaging mission of SIs international partner in Europe. It carries an optical imaging system with a resolution of 2.5 m for panchromatic and 5.0 m for multispectral bands as the primary payload. The satellite was launched in December 2012.

     

    SI PARTICIPATION

    SI is contracted to develop the primary payload of the above-mentioned small satellite and attitude determination and control systems such as sun sensors and magnetometers. SI is scheduled to develop SM, STM, QM and FM of the primary payload and deliver SM, STM and FM to its international partner.

     

    EOS-C SYSTEM VERSION 3.0

    EOS-C System Version 3.0 is the modified version of EOS-C system that has flight heritage from RazakSAT of Malaysia and DubaiSat-1 of UAE. EOS-C System Version 3.0 is a push-broom type camera with 2.5 m GSD for panchromatic and 5.0 m GSD for four multi-spectral bands in visible and near infrared spectrum. The swath width of the generated image is 20 km. 64 Gbits of solid-state recorder is implemented for image data storage. Mass of the payload is less than 41 kg and peak power consumption with all heaters on is less than 69 W.


    PERFORMANCE SUMMARY OF EOS-C SYSTEM VERSION 3.0

        Parameter

    Feature

    Remarks

        Mass

    < 41 kg

    Optics < 35 kg, Electronics < 6 kg

        Spectral Bands

    PAN + 4 MS

    PAN + RGB, NIR

        Resolution

    PAN: 2.5 m, MS: 5 m (@ 700 km)

    SSO

        Swath-width

    20 km (@ 700 km)

     

        Physical Dimension

    Optics: 492 x 985 mm

     

      

    Electronics: 200 x 200 x 220 mm

     

     

     



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  • DubaiSat-2

  • DubaiSat-2 is the second Earth observation small satellite of UAE. Emirates Institute for Advanced Science and Technology (EIAST) is currently developing DubaiSat-2 with SI in continuation of DubaiSat-1 project. DubaiSat-2 is technologically more advanced than its predecessor and will have better commercial applications. The cutting-edge small satellite of UAE will be ready for launch in 2012.

     



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  • KOMPSAT-1

  • Korea Multi-Purpose Satellite-1 (KOMPSAT-1) is a 460 kg Earth observation satellite developed by Korea Aerospace Research Institute (KARI) under the Korean National Space Development Program. KOMPSAT-1 accommodates Electro-Optical Camera (EOC) of 6.6 m resolution panchromatic images, Ocean Scanning Multi-Spectral Imager (OSMI) of 1 km resolution multi-spectral images, Ionosphere Measurement Sensor (IMS) and High Energy Particle Detector (HEPD). It was launched by American Taurus launch vehicle on December 21, 1999.

     

    SI PARTICIPATION

    SI was contracted by KARI to develop Direct Archiving Subsystem (DAS) and Catalog and Product Generation software (CAP) for KOMSAT-1 Image Receiving and Processing Station (IRPS) and installed the system for Korean government and UAE.

     

    DIRECT ARCHIVING SUBSYSTEM (DAS) & CATALOG PRODUCT GENERATION SOFTWARE (CAP)
    DAS is to receive image data from KOMPSAT-1 and archive the data in Data Recording Card (DRC) which SI developed in house. CAP is to generate Level Product and catalog by radiometric correction, systematic/precision geocoding and ortho-rectification.


     

     



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  • KOMPSAT-2

  • KOMPSAT-2 is an 800 kg class Earth observation satellite developed under the Korean National Space Development Program. KOMPSAT-2 has the capability of 1 meter resolution imaging with 15 km swath-width at 685 km altitude. KOMPSAT-2 was launched on July 28, 2006 in Russia.

     

    SI PARTICIPATION

    SI developed Precision Altitude Determination (PADS) and Image Receiving and Processing Station (IRPS) of KOMSAT-2 for KARI and installed the system for Korean government, KARI and UAE.

     

    KOMPSAT-2 PRECISION ATTITUDE DETERMINATION (PADS)

    PADS is a software package which performs precision attitude determination by using precise orbit data and attitude sensor data (star trackers and gyros). This software estimates all sensitive parameters including misalignment angle between each sensor and optical bench, the drift rate error and scale factor error of each gyro and etc. PADS includes simulated sensor data generator, data analysis tools, validation tools as well as animation tools.

     

    KOMPSAT-2 IMAGE RECEIVING AND PROCESSING STATION (IRPS)

    SI was contracted by KARI for developing IRPS of KOMPSAT-2. KOMPSAT-2 IRPS receives and archives KOMPSAT-2 Images and produces image products and builds a database. It also provides user-friendly Web services for image search, browsing and order management. For the satellite imaging operation, IRPS generates imaging plans based on users requests, and forwards the plans to Mission Control Station (MCS).

     

     



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  • KOMPSAT-3

  • KOMPSAT-3 is a 970 kg Earth observation satellite that provides high resolution images in panchromatic and multispectral bands. KOMPSAT-3 was developed leadingly by KARI and launched on May 18, 2012.

     

    SI PARTICIPATION

    SI provided the Development Model (DM) of power controller, and on-board computer processor module as well as six FM coarse sun sensors to KARI. Image Receiving and Processing Station and several key subsystems of Mission Control Station is currently being developed.

    ON-BOARD COMPUTER PROCESSOR MODULE

    SI developed On-board processor module with reliable RTOS and high-end CPU. SI developed a space qualified processor module based on TSC695F CPU (ERC32).

     

    KOMPSAT-3 PRECISION ATTITUDE DETERMINATION (PADS)

    SI is contracted by KARI for developing Precision Attitude Determination of KOMPSAT-3. PADS is a software package which performs precision attitude determination by using precise orbit data and attitude sensor data (star trackers and gyros). This software estimates all sensitive parameters including misalignment angle between each sensor and optical bench, the drift rate error and scale factor error of each gyro and etc. PADS includes simulated sensor data generator, data analysis tools, validation tools as well as animation tools.

     

    KOMPSAT-3 IMAGE RECEIVING AND PROCESSING STATION (IRPS)

    SI is currently developing KOMPSAT-3 Image Receiving and Processing Station (IRPS). SI IRPS consists of four subsystems; User Interface Subsystem (UIS), Image Collection Planning Subsystem (ICPS), Direct Ingestion Subsystem (DIS) and Product Management Subsystem (PMS). UIS is to process Product Order of the External User. It virtualizes convenient operator interface to manage orders from end-users and end-user interface such as catalog searching, order placing, order status monitoring and product download.

    Web-based end-user interface                                               Application-based operator interface        


    ICPS is to process Image Collection Request from the UIS and to generate the Image Collection Plan. Also, ICPS is in charge of the interface with the Primary Mission Control Station (MCS)
    .

    DIS is to receive KOMPSAT-3 Bitstream Data from the Antenna & RF Equipment and retrieve KOMPSAT-3 CADU Data.  Also, DIS archives KOMPSAT-3 CADU Data and/or Bitstream Data in real time. During image transmission, taken images are checked on real-time moving window display. 
    PMS is to generate Level Product and archive Level Product, Meta data and manage database.


    KOMPSAT-3 FLIGHT DYNAMICS SOFTWARE (FDS)

    Flight Dynamics Software is a key subsystem of Mission Control Station for KOMPSAT-3. KOMPSAT-3 FDS is PC/Linux or PC/Windows based and its main functions are orbit prediction and determination, event prediction and fuel accounting.

     

    KOMPSAT-3 MISSION PLANNING SUBSYSTEM (MPS)

    KOMPSAT-3 MPS is PC/Linux based and its main functions are event prediction and mission scheduling.

     

     



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  • KOMPSAT-3A

  • KOMPSAT-3A is Koreas first EO/IR satellite with two imaging systems on board; KOMPSAT-3A Infrared Sensor System (KISS) and Panchromatic EO payload. It is currently under development leadingly by Korea Aerospace Research Institute (KARI) and its launch is planned in 2014.


    SI PARTICIPATION

    SI participated in manufacturing and supplying six FM coarse sun sensors and a telescope ground model for the IR sensor module verification of KOMPSAT-3A.


    TELESCOPE FOR KOMPSAT-3A IR SENSOR MODULE VERIFICATION

    SI manufactured a telescope to test KOMPSAT-3A IR sensor on the ground and completed delivering the telescope in late 2009. It is the same configuration of KOMPSAT-3 telescope which is 4-mirror Korsch telescope. It is composed of Zerodour mirrors and CFRP metering structure.

     



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  • KOMPSAT-5

  • COMPSAT-5 is the first Korean Synthetic Aperture Radar (SAR) satellite which provides high quality SAR images in all weather and light conditions.  KOMPSAT-5 will reach Dawn-Dusk orbit between an altitude of 500 km to 600 km in 2013.

     

    SI PARTICIPATION

    SI manufactured and supplied Sun Sensors (6 CSSA) and is currently developing Image Receiving and Processing Station (IRPS), Flight Dynamics Subsystem of Mission Control Station and Transportable Ground Station for KOMPSAT-5.

     

    KOMPSAT-5 FLIGHT DYNAMICS SUBSYSTEM (FDS)

    It is PC/Linux or PC/Windows based and its main functions are orbit prediction and determination, event prediction and fuel accounting.

     



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  • COMS-1

  • COMS-1 is a geostationary satellite of 2.5 tons, which was built by KARI jointly with EADS Astrium. COMS-1 accommodates three payloads; Communication Payload, Meteorology Imager (MI) and Geostationary Ocean Color Imager (GOCI). COMS-1 was successfully launched from Kourou, French Guiana by Ariane 5 on 25th of June, 2010.

     

    SI PARTICIPATION

    SI developed Ka-band communication payload system in cooperation with Electronics and Telecommunications Research Institute (ETRI) and key subsystems of Image Receiving and Processing Station (IRPS) and Mission Control Station (MCS) for COMS-1. In addition, SI developed some components such as Digital Control Unit (DCU), DC/DC Converter, Sun Sensors and GOCI EGSE.

     

    COMS-1 KA-BAND COMMUNICATION PAYLOAD

    To meet in-orbit verification mission of Ka-band communication payload technology developed by domestic institutes, SI developed Ka-band Beam Switching Transponder cooperatively with ETRI and integrated and tested the system. In addition, SI developed core RF equipment for the payload. The Ka-Band payload provides three regional beams simultaneously and the beam switching function for high speed multimedia services including the internet via satellite in the public communications network for all coverage.

     

     

    COMS-1 FLIGHT DYNAMICS SUBSYSTEM (FDS)

    SI developed flight dynamics subsystem which is the key subsystem of Ground Control System for COMS-1. It is PC/Windows/.NET based and its main functions are orbit prediction and determination, station keeping and relocation, event prediction and fuel accounting.

     

     

    COMS-1 IMAGE NAVIGATION AND REGISTRATION SW MODULE (INRSM)

    SI was contracted to develop INRSM of COMS-1 Image Receiving and Processing Station (IRPS) by EADS Astrium, the prime contractor for COMS-1. Data from COMS-1 payloads, MI and GOCI, is navigated and registered automatically in near real-time by INRSM software at COMS image receiving and processing ground station.

     

    COMS-1 IMAGE PREPROCESSING SUBSYSTEM (IMPS)

    SI developed and supplied Image Preprocessing Subsystem (IMPS) for COMS-1 IRPS to KARI. IMPS is to receive and process image data at ground control station. It also generates Level Products, which are classified into raw image, LV0, LV1A and LV1B HDF, by Image Radiometric Correction Module and manage them.


    COMS-1 DIGITAL CONTROL UNIT (DCU)

    Digital Control Unit is to do telecommunications between communication payload and bus. DCU of COMS-1 equips MSM (MMU (Memory Management Unit) storage module) switch control to change RF switch state and serial bus interface to monitor and control DCU. In addition, DCU provides DC power to MSM for switch operation.

     

    COMS-1 DC/DC CONVERTER

    DC/DC Converter regulates DC voltages (+5 V, -5 V, +8 V, -8 V, +15 V) from MPIU bus voltage (+50 V). DC regulation is under +/-2 % at EOL including line and load stability, temperature variation, aging and radiation. The module includes primary and secondary DC/DC converter module in the box.

     

    COMS-1 SUN SENSOR

    SI was contracted to provide sun sensors for COMS-1 by EADS Astrium. SI manufactured two types of sun sensors, BASS and LIASS. BASS is Bi-axis sun sensor which is wide-angle sun sensor to perform the sun acquisition/pointing and pyramidal block with the angles of 7 arc degrees. LIASS is Linear Accurate Sun Sensor which is used as sun detection device in order to have an absolute reference when controlling the spacecraft.

     

    COMS-1 GOCI ELECTRICAL GROUND SUPPORT EQUIPMENT (EGSE)

    SI developed GSE system for Geostationary Ocean Color Imager (GOCI) boarded COMS-1. Its main functions are test preparation, real time function, post processing and data archiving, image data processing and display and self test function. It has 19 equipment in a 36U cabinet which is CE certified.

     

     



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  • KSLV-1

  • KSLV-1 is Koreas first launch vehicle designed for a 100 kg class Low Earth Orbit (LEO) satellite. KARI has taken the responsibility of the entire program in cooperation with Russia for the first stage of the rocket development. Two models of KSLV-1 were launched from the Naro Space Center of Korea respectively in August, 2009 and June, 2010.

     

    SI PARTICIPATION

    SI developed and provided a video/audio monitoring system for KSLV-1 to KARI. This system consists of compact video cameras, video compression units and video expansion units. It is able to be operated in acceleration condition up to 12 G. This rocket camera also can be used for aircrafts as well as space launch vehicles. Main features of the system are summarized as follows.

     

    VIDEO CAMERA UNIT
       Small, Rugged, Vibration Damping Structure

       NF Mount Small Size Lens

       768x494 pixel CCD

       NTSC, S-Video Output

       Operation Acceleration < 12G


    VIDEO COMPRESSION UNIT

       Two Video, two Audio Inputs

       JPEG2000 Compression

       Interleaving Packet Format

       RS-Encoding

       Variable Transmission Speed

       Adaptive LPF


    VIDEO EXPANSION UNIT

     


         Data Archive and Display

         JEPG2000 Decompression

         Portable Rack Mount

     

     

     


     

     



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  • Defence Systems

  •  
  • AUTOMATIC VIDEO TRACKER OF NEXT GENERATION TANK

  • Automatic Video Tracker of Next Generation Tank was designed to automatically track the target vehicle with DSP-based real-time image processing system. The Automatic Video Tracker is high performance image processor that supports parallel image processing and 30 Hz real-time tracking algorithm processing. Application areas of Automatic Video Tracker are fire control (gun pointing), missile guidance and surveillance.

          
    Context Diagram                                             Output Image          

     



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  • VIDEO COMMUNICATION SYSTEM OF DEFENSE ROBOT

  • Video Communication System of Defense Robot was designed to optimize real-time streaming of a defense robot for real-time remote control. Video Communication consists of two units; Video Compression Unit (VCU) and Video Expansion Unit (VEU). Total video time delay is about 100ms (Wireless -LAN communication) and images in 5 channels are compressed, transmitted, received, decompressed and displayed in real-time.

    Context Diagram

     



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