• Journal of Satellite, Information and Communications
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• v.1 no.2
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• pp.16-24
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• 2006

As a multi-mission GEO satellite, COMS system is being developed jointly by KARI, ETRI, KORDI, KMA, and industries from both abroad and domestic. EADS ASRTIUM is the prime contractor for manufacturing the COMS. ETRI is developing the COMS Ka-band payload and SGCS with the fund from MIC. COMS Satellite Ground Control System (SGCS) will be the only system for monitor and control of the satellite in orbit. In order to fulfill the mission operations of the three payloads and spacecraft bus, COMS SGCS performs telemetry reception and processing, satellite tracking and ranging, command generation and transmission, satellite mission planning, flight dynamics operations, and satellite simulation, By the proper functional allocations, COMS SGCS is divided into five subsystems such as TTC, ROS, MPS, FDS, and CSS. In this paper, functional design of the COMS SGCS is described as five subsystems and the interfaces among the subsystems.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.25 no.11
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• pp.1142-1155
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• 2014

The classical PCM/PSK/PM scheme has been commonly used for TC & R applications between satellites and ground stations in the S-band. We analyzed TC & R link performance between ground station and the geostationary satellite which employs PCM/PSK/PM, when the satellite are particularly on the Super Synchronous Transfer Orbit(SSTO). The satellite parameters on SSTO are assumed to be those operating on the geostationary orbit, considering heritage aspect. In the uplink, the results shown indicate that sufficient margins over 3 dB are obtained when the EIRP of ground station is greater than 65 dBW. The down link performance is of great interest. By adjusting the telemetry modulation index and ranging modulation index, we could obtain the required margin of 3.0 dB in the down link, and find out the minimum G/T of ground station. In conclusion, the previously operated ground stations during LEOP at COMS launch, can be operational when GEO injection is made using SSTO(65,000 km and 70,000 km).

• Journal of Positioning, Navigation, and Timing
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• v.13 no.2
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• pp.199-206
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• 2024

The GEO-KOMPSAT-2A (GK2A) satellite, which was launched in December 2018, carries weather observation payloads and uses the image navigation and registration system to calibrate the observation images. The calibration system requires accurate orbit prediction data and depends on the accuracy of the orbit determination accuracy. In order to find a possible way to improve the current orbit determination accuracy of the GK2A flight dynamic subsystem module, orbit determination software was developed to independently evaluate the orbit determination accuracy. A comprehensive satellite dynamic model is applied for a batch-type least squares filter. When determining the orbit, thrust firing during station-keeping maneuvers and wheel-off loading maneuvers is taken into account. One month of GK2A ranging data were processed to estimate the satellite position on a daily basis. The orbit determination error was evaluated by comparing estimates during overlapping estimation intervals.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.99-107
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• 2008

The COMS is a kind of geostationary multi-functional satellites with three different mission objectives. Two of them aim at earth observation and the COMS has two optical payloads according to those missions. The payloads are composed of a meteo imager and an ocean color imager, and their inherent characteristics require optimal interface design for their performance to be concurrently achieved. Therefore, various kinds of constraints are considered in their component accommodation on the COMS platform. This paper shows a general overview of the optical payload accommodation design and describes the design consideration to achieve the optimized performance from thermal and mechanical point of view.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.26 no.11B
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• pp.1573-1582
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• 2001

In this paper we analyze the main resources of error in GEO-satellite STFS(Standard Time & frequency Signal) dissemination system. For the case of small countries like Korea, we compare GEO-satellite STFS dissemination technique with the terrestrial network or with the GPS using LEO-satellites, and analyze its advantages over the forementioned systems. We also introduce the GEO-satellite STFS dissemination systems which are being developed or in service. Particularly, we put much efforts to develop the synchronization error calibration technique required to provide a highly accurate STFS service via KoreaSAT. We then propose the differential mode technique as the most effective and efficient calibration technique for mitigating errors in GEO-satellite STFS dissemination systems, and analyze its performance via computer simulation. We also analyze the relation between time accuracy and frequency accuracy. Our experimental results show that the time accuracy is better than 100 ns and the frequency accuracy is better than 10-13 over 7 days all around Korea peninsula. Finally, we propose methods to improve the performance of STFS dissemination system, and demonstrate that the proposed methods result in more accurate synchronization of GEO-satellite STFS.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.33-40
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• 2009

In this paper, the preliminary EMC analysis process between the Communication, Ocean and Meteorological Satellite (COMS) and Geostationary Earth Orbit (GEO) launch vehicles in the frequency range [1MHz-47MHz] is described. The launch vehicle Radiated Emission (RE) specifications have been compared to COMS satellite Radiated Susceptibility (RS) limits. The COMS RS limits are the RS qualification levels of COMS units during launch. The negative margins appear between land launch or soyuz launch vehicle RE and COMS RS. Then, if the land launch or soyuz is chosen by the customer, The tests should be performed at satellite level in order to demonstrate the compatibility with respect to launch vehicles specifications.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.8
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• pp.674-682
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• 2014

Radio Frequency Test Set (RFTS) is essential to verify Telemetry, Command & Ranging (TC&R) RF subsystem of both Low Earth Orbit (LEO) and Geostationary Earth Orbit (GEO) satellite during Assembly Integration & Test (AI&T). The existing RFTS was specialized for each project and needed to be modified for each new satellite. The new design enables RFTS to be used in various projects. The hardware and software was designed considering this and therefore it could be directly used in other projects within a similar test period without modification or inconvenience. It will be also easily controlled, modified, and managed through the extension in modularization according to each function and the use of COTS (commercial on-the-self) and this will improve system reliability. A more reliable RF test measurement is also provided in this new RFTS by using an accurate reference clock signal.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.2
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• pp.157-164
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• 2007

Launch Interface Ring roles as connection department of satellite and launcher for to deliver all structure loads that occur from the satellite, and one of the most intensive load received parts. Especially COMS, the first Korean developing GEO satellite, needs Launch Interface Ring with Tank Support Beam because of dissymmetry fuel tanks. The purpose of this study is the suitable form decision of Launch Interface Ring at preliminary design of COMS. In this study, launch mass and design constraints are investigated. Moreover, optimization algorithm and simplification technique are used. At the beginning of this study, three types of launch interface ring were presented and finally model 3 was the lightest design for resistance of launch environment. Nevertheless, model 1 can be suggested for application to COMS because of the satellite gravity center control and ease of fabrication.

• Journal of Satellite, Information and Communications
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• v.11 no.4
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• pp.10-14
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• 2016

Korean satellite development projects were divided military objectives such as national security, and commercial communication satellites. The First geostationary Korean earth observation satellite, GeoKOMPSAT is a turning point to concern another way to utilizing satellite. In the past, the main concern was the sharp ground images, now days, it is more important to make high added value from satellite data. In particular, environmental payload, GEMS mounted on the satellite GeoKOMPSAT-2 will monitor air quality which is not observed by visual material, may be referred to as case by utilizing the satellite. Satellite data utilization is likely to receive a great influence on the appropriate public policy data. If the public is expected to be fully revealed that potential demand. It is time to change the management policy on the security aspects of weak satellite data. Depending on the expanding use of satellites, it is necessary to investigate the status of disclosing satellite data, and suggests policy options for the distribution of materials for the environment satellite characteristics.

• The Bulletin of The Korean Astronomical Society
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• v.39 no.1
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• pp.53.1-53.1
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• 2014

본 연구에서는 고궤도 및 원거리 우주물체의 추적 및 관측이 용이한 광학관측 시스템을 이용하여 정지궤도위성을 관측하였고, 광도곡선 분석을 통해 식별정보를 획득하였다. 정지궤도 위성은 자세에어 방법에 따라 회전 안정화 위성과 3축 안정화 위성으로 나뉘며, 3축 안정화 위성은 다시 통신위성과 지구관측 위성 등으로 나뉜다. 회전 안정화 위성의 식별 연구를 위해 중국의 FY-2 위성을 관측대상으로 선정하였고, 3축 안정화 위성의 식별을 위해 한국의 COMS-1 위성을 관측 대상으로 선정하였다. 회전안정화 위성은 Sidereal Tracking Mode로 관측하면 위성의 궤적이 선 모양으로 나타난다. 이때 나타난 궤적의 pixel value 값을 확인하면 일정한 주기로 밝기가 변화 하는 것을 확인할 수 있으며, FFT를 수행하면 위성의 회전율과 회전 주기를 구할 수 있다. 3축 안정화 위성은 Stare Mode로 관측하여 측광하면 광도곡선을 획득할 수 있다. 위성의 형상을 결정하는 본체, 안테나, 태양전지판을 모델링하여 광도곡선 시뮬레이션결과와 비교하면 각각의 형상이 광도곡선에 미치는 영향과 특징을 알 수 있고, 이를 통해 식별정보를 획득할 수 있다. 이상의 분석을 통해 얻은 FY-2위성과 COMS-1 위성의 식별정보를 제시하고 향후 우주물체 식별 연구에 활용하고자 한다.