A core (or equipment) module houses the housekeeping functions - power, telemetry and data handling, attitude control - needed on all space missions. POD (Precise Orbit Determination) accuracy, - S-band for TT&C data transmissions 2008, URL: http://www.spacemart.com/reports/SKorea_decides_to_terminate_satellite_space_agency_999.html, 6) http://www.spacedaily.com/reports/South_Korea_Confirms_Contact_With_Satellite_Lost_999.html, 7) Ok-Chul Jung, Dae-Won Chung, Sun-Ju Park, Dae-Hwan Hyun, Yong-Sik Chun, “Advanced Concept and Design of the Multi-satellite Operations System,” Proceedings of the SpaceOps 2010 Conference, Huntsville, ALA, USA, April 25-30, 2010, paper: AIAA 2010-2333, 8) Information provided by Hae-Dong Kim of KARI, Daejeon, Korea, 9) Hyo-Suk Lim, “Applications of KOMPSAT Data and Space Program of Korea,” URL: http://www.aprsaf.org/data/vietnam_ws/vws_14.pdf. The KOMPSAT-6 external interfaces include the King Sejong station on Antarctica to support urgent imaging request with looking mode change and contingency support, additional ground stations in support of LEOP (Launch and Early Orbit Phase), and the IGS (International GPS Service) data center providing high accuracy ground based GPS data products to KARI for POD (Precision Orbit Determination) processing. Lee, “On-Board Management of Multiple Processor Spacecraft System,” Proceedings of the IEEE Aerospace Conference, Big Sky, MT, Mar. 5). The Deajeon station in South Korea is responsible for tasking the satellite. The KOMPSAT-6 ground segment is to be operated based on mission operation procedures in support for mission scheduling and planning activities and observation data reception and processing activities. Orbit: Sun-synchronous circular polar orbit, altitude = 685 km, inclination = 98.13º, period = 98.46 min, local equatorial crossing on ascending node at 10:50 hours, 14 17/28 orbits per day, revisit time = 28 days. These key functions of the MCE are summarized as follows: • Communication with KOMPSAT-6 satellite via S-band RF link, • Mission Activity Planning and Command Procedure Planning, • Orbit Determination, Prediction, and Maintenance, Figure 17: Architecture and interfaces of the KOMPSAT-6 ground segment (image credit: KARI). It also manages radar timing control and redundancy configuration of SSS. Operation Modes of Solar Array Regulator: The solar array regulator has three operational modes depending on the voltage of the unregulated primary power (100 V) bus and output power of the solar panels. 1) 2) 3), Figure 1: Artist's view of the KOMPSAT-1 spacecraft in orbit (image credit: KARI). KOMPSAT-6 EPS design: The new designs for the KOMPSAT-6 are the power limit mode for the solar array regulator protection, DNEL and UV concept for battery protection, the buckbooster converter scheme for solar array regulator, and 100 V bus voltage implementation for SAR payload high power consumption demand. S-band Transponder, Units for System Stand-by - Normally dark calibration before and after image The solar array regulator comparison for the heritage program and the KOMPSAT-6 is summarized in Table 3. The mechanical design assumes a spacecraft manufacturing tolerance of ±0.1 mm. According to the requirement analysis, the ground segment is designed to be comprised of three elements, which consist of the MCE (Mission Control Element) , IRPE (Image Reception and Processing Element) and the CE (Calibration Element), respectively. Arirang-2 (COSPAR 2006-031A) orbits at a height of 685 kilometers, circling the Earth 14 times per day, and is expected to maintain that orbit for 3 years. A third module, housing a monopropellant hydrazine propulsion system, provides on-orbit thrust and station-keeping. In addition, ground reference targets of known brightness can be used for white calibration. - Stored for minimum 35 days mission, Figure 7: Observation concept of OSMI (image credit: KARI), The SPS package consists of two instruments: HEPD (High Energy Particle Detector) and IMS (Ionosphere Measurement Sensor). Battery: The battery accepts and stores the electrical energy from the solar array. The SAA is an active phased array and it is able to operate different beam characteristics for transmission and reception. Initial reviews pointed toward a possible machinery malfunction or a misalignment that may have affected power generation. OSMI is a whiskbroom-type imager generating imagery in up to six spectral bands (in the region of 400 - 900 nm) with a capability for bandwidth and band center selection on command. 301-306, 11) Kim Bang, Woosug Cho, “KOMPSAT-EOC Sensor Model Analysis,” URL: http://www.fig.net/pub/proceedings/korea/full-papers/pdf/session4/bang-cho.pdf. - PES identifies the particle types detected and measures their energy in seven channels. The power interface between the PCDU and the APS (Antenna Power Supply) was optimized to minimize the power loss as shown in Figure 10. - Comments and corrections to this article are always welcome for further updates. • The spacecraft bus shall provide the required power for the continuously 150 second imaging operation of SSS per every orbit where no eclipse occurs in orbit time frame. The South Korean KOMPSAT-2 Earth-imaging satellite was developed by KARI (Korea Aerospace Research Institute), in partnership with EADS Astrium, to assure continuity with the KOMPSAT-1 satellite launched in 1999. … Figure 13: Electrical interfaces between the AIS receiver and the PCDU/IBMU (image credit: ETRI), Mechanical Interface Design: The mechanical interfaces design has been carried out for the AIS receiver and the AIS antennas mounting on the spacecraft. KOMPSAT-2 operates in a near-polar, circular Sun-synchronous orbit. On satellite Eutelsat Hot Bird 13º East you have KBS HD, Arirang SD and CGN SD as indicated on the table above. The DLS comprises all the functions necessary for acquisition, storage and handling of data generated by the SSS, and for real-time or near real-time transmission to the ground station. XSAR is a multi-mode operations instrument consisting of the SSS (SAR Sensor Subsystem), the DLS (Data Link Subsystem) and the PLM (Payload Module). The AIS receivers are able to operate in both frequency spectrum capture modes (Raw/OGP) and on-board processing (OBP) mode allowing simultaneous operation.
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