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ROCSAT-1 Satellite Program And OCI Sensor Update

ROCSAT-1 Satellite Program And OCI Sensor Update. Paul Cheng-I Chen National Space Program Office July 24,1998. To support national aspiration to build-up capability of developing a large-scale, high-quality, integrated system by carrying out a two-phase ROCSAT space program

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ROCSAT-1 Satellite Program And OCI Sensor Update

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  1. ROCSAT-1 Satellite Program And OCI Sensor Update Paul Cheng-I Chen National Space Program Office July 24,1998

  2. To support national aspiration to build-up capability of developing a large-scale, high-quality, integrated system by carrying out a two-phase ROCSAT space program To establish the organizational and technical infrastructure necessary for executing a national space program To build the human resources and capabilities necessary to support the space program To promote the space science research of domestic universities and to upgrade the technology base of local industry To position us as an active and contributory member in international space community by participating in international cooperative projects GOALS • National Space Program Office (NSPO), established in 1991, is a governmental agency to execute a 15 years (1991-2006) long term space program and to achieve the following goals:

  3. Phase I (1991-1997) Establish the National Space Program Office (NSPO) to execute the 15-year space technology development plan. Develop the infrastructure necessary to carry out the space program. Incorporate with existing organizations relevant to space science and/or technology. Establish the infrastructure and acquire the basic technology of space systems through close cooperation with experienced foreign contractors. Emphasize technology transfer in support of NSPO long-term goal of space technology build-up especially in the areas of systems engineering, spacecraft design and manufacture, and system integration and test. ROCSAT-1 mission: - To successfully develop, launch, and operate a low earth orbit (LEO) scientific satellite. - To conduct three scientific and technology experiments in the areas of ocean color imaging, space telecommunications, and solar-terrestrial physics. APPROACH

  4. Phase II (1998-2006) Develop small-class satellites operated in LEO during the nine years of Phase II. Select missions based on practical applications to fulfill the civilian needs and to further scientific exploration. Employ acquisition strategy incorporating the infrastructure and technology established in ROCSAT-1 program. Participate in the international cooperation programs to progressively build the capability of NSPO and to promote our space research and industry. APPROACH (Continued)

  5. ROCSAT-1

  6. ROCSAT-1 System and Its Related Operational Segments Overseas Remote Tracking and Control Stations (Bangalore, India and Maurituis) Payload Module Bus Satellite Integration and Test Facility TT&C Stations (Kueijen and Chungli) Mission Control Center (Hsin-Chu) Launch Vehicle System Science Data Distribution Center (Keelung/Chungli/ Hsin-Chu) Domestic Components

  7. ROCSAT-1 SPACECRAFT CONFIGURATION • IPEI • OCI • ECP • PAYLOAD MODULE • CORE MODULE • RCS MODULE • ADAPTER CONE • SOLAR PANEL

  8. ROCSAT-1 SPACECRAFT • Total Weight : 395 kg • Total Payload Weight : 48 kg • Total Power : 450W at end of life (EOL) • Dimensions : 2.1m * 1.1m (7.2m with solar array deployed) • Stabilization: Three-Axis stabilized • Down Link Data Rate : 1.4 Mbps • Reliability : 0.9 at the end of 2 year mission • Mission Life : 2 Years • Design Life : 4 Years • Manufacturer : TRW (USA)

  9. Domestic Components Antenna Remote Interface Unit On-board Computer Solar Array Panel Assembly Filter/Diplexer

  10. ROCSAT-1 SCIENTIFIC PAYLOADS Ionospheric Plasma and Electrodynamics Instrument (IPEI) Ocean Color Imager (OCI) Payload Adapter Experimental Communication Payload (ECP)

  11. Conduct in situ measurement of plasma processes (ion temperature, drift velocity, and density fluctuation) in the low-latitude ionosphere. Data may be used for study of ionospheric effect on radio communication. A science team consisting of local investigators and University of Texas, Dallas (UTD) scientists will perform data processing & analysis. Hardware is built by UTD and TRW. IONOSPHERIC PLASMA AND ELECTRODYNAMICS INSTRUMENT (IPEI)

  12. IONOSPHERIC PLASMA AND ELECTRODYNAMICS INSTRUMENT (IPEI) Ion Trap (IT) (Vertical/ Horizontal) Drift Meter Main Electronics Package (MEP) Retarding Potential Analyzer (RPA) Sensor Electronic Package (SEP)

  13. IPEI INSTRUMENT FEATURES

  14. Conduct communication experiments using Ka-band communication subsystem EXPERIMENTAL COMMUNICATION PAYLOAD (ECP) • . Multimedia experiment • . Propagation & Rainfall attenuation experiment • . Digital communication experiments • . Voice, Fax and Data communication experiment Space segment of the ECP is designed and built by our MTI and Japanese NEC

  15. EXPERIMENTAL COMMUNICATION PAYLOAD (ECP) Payload Adapter Transmitter Input Filter Transmit Antenna Microwave Switch Low-noise Amplifier Channel Filter Receive Antenna Down Converter

  16. ECP INSTRUMENT CHARACTERISTICS

  17. Conduct oceanic pigment study to better understand the lower latitude area marine food chain and the ecosystem. A science team consisting of local & foreign researchers will perform calibration, data processing & analysis. Data will be available to international scientific community. Hardware is constructed by NEC, Japan. OCEAN COLOR IMAGER (OCI)

  18. OCEAN COLOR IMAGER (OCI) Main Electronic Unit Camera Head Focal Plane Array Analog Electronic Unit

  19. OCI INSTRUMENT CHARACTERISTICS

  20. Thomson’s TH7811 CCD with 1728 elements 896 pixels Central 64 pixels are high resolution Integration time 115.8ms IFOV 800m Adjustable antiblooming voltage OCI Characteristics(Cont..)

  21. Push Broom Scheme

  22. OCI Functional Block Diagram

  23. Optical Path

  24. OCI Optical Characteristics

  25. CCD Responsivity

  26. OCI Performance

  27. OCI Operational Mode

  28. OCI Mode Flow

  29. Geometric Characteristics Test

  30. Geometric Characteristics Test

  31. Radiometric Characteristics Test

  32. I&T BUILDING

  33. An integration & test (I&T) building capable of simultaneously conducting I&T of two satellites of up to 1500 kg each. Major testing instruments and equipments including Thermal Vacuum Chamber, EMI/EMC Anechoic Chamber, Acoustic Chamber, Vibration Shakers, Mass Property Measurement Instrument, and etc. Spacecraft & payload instruments were delivered to NSPO in May 1997 for integration & test. INTEGRATION & TEST FACILITIES

  34. ROCSAT-1 Communication Network

  35. TT&C Station

  36. MOC

  37. ROCSAT-1 LAUNCH SERVICE • Launch services : Direct insertion to mission orbit • Launch Vehicle : ATHENA 1 • Launch Site : Cape Canaveral, Florida

  38. ROCSAT-1 Orbit (600 km, 35 deg) • Period: 96.69 min • Mean Motion: 14.89 rev/day • Velocity: 7.56 km/sec • Daily Ground Contact Time Above 10 deg Elevation: ~7 min x 6

  39. ROCSAT-1 Groundtracks

  40. Variation of Latitude Coverage Due to the Orbit Precession Taiwan s Latitude

  41. 17-Day Gap Variation of OCI Coverage Over Taiwan Above10-deg Elevation During Daytime (9:00~15:00)

  42. Variation of OCI Coverage

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