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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 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 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:
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
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)
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
ROCSAT-1 SPACECRAFT CONFIGURATION • IPEI • OCI • ECP • PAYLOAD MODULE • CORE MODULE • RCS MODULE • ADAPTER CONE • SOLAR PANEL
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)
Domestic Components Antenna Remote Interface Unit On-board Computer Solar Array Panel Assembly Filter/Diplexer
ROCSAT-1 SCIENTIFIC PAYLOADS Ionospheric Plasma and Electrodynamics Instrument (IPEI) Ocean Color Imager (OCI) Payload Adapter Experimental Communication Payload (ECP)
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)
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)
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
EXPERIMENTAL COMMUNICATION PAYLOAD (ECP) Payload Adapter Transmitter Input Filter Transmit Antenna Microwave Switch Low-noise Amplifier Channel Filter Receive Antenna Down Converter
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)
OCEAN COLOR IMAGER (OCI) Main Electronic Unit Camera Head Focal Plane Array Analog Electronic Unit
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..)
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
ROCSAT-1 LAUNCH SERVICE • Launch services : Direct insertion to mission orbit • Launch Vehicle : ATHENA 1 • Launch Site : Cape Canaveral, Florida
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
Variation of Latitude Coverage Due to the Orbit Precession Taiwan s Latitude
17-Day Gap Variation of OCI Coverage Over Taiwan Above10-deg Elevation During Daytime (9:00~15:00)