• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.8
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• pp.747-752
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• 2007

Domestic satellite development programme is generally classified into two categories: COMS as GEO satellite and KOMPSAT as LEO one. Each satellite has the on-board propulsion system fulfilling its own mission requirements. The COMS propulsion system provides the thrust and torque required for the insertion into GEO, attitude and orbit control/adjustment of spacecraft. It is the well-known Chemical Propulsion System(CPS) using bipropellants. On the other hand, the monopropellant propulsion system is employed in KOMPSAT, and its main role is on-station attitude control excluding the orbit transfer function. In this study, these two representative propulsion systems are compared and analysed as well, in terms of essential differences and important characteristics.

• Journal of Astronomy and Space Sciences
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• v.19 no.4
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• pp.385-394
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• 2002

Satellite laser ranging is a technique for precisely measuring the range between a laser station and a satellite that is equipped with retro-reflectors. SLR technique was first used for Beacon-B satellite in 1964 with the ranging accuracy of meter level. Now the single shot have centimeter level accuracy and the normal point have mm level in ranging. In this study we developed the algorithm for precise orbit determination using SLR data and performed the orbit determination of GPS-36 satellite using the algorithm. RMS of the estimated orbit was 74cm when compared with IGS precise orbit. It is known that RMS of SLR measurement residual is below 55mm. But we were able to achieve 44mm RMS of residual throughout this study.

• Korean Journal of Remote Sensing
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• v.34 no.3
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• pp.565-578
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• 2018

In this paper, we investigate the feasibility of modelling image strips, instead of individual scenes, that have been acquired from the same orbital pass through the process of bundle adjustments. Under this approach, First, a rational function model (RFM) of the strip image is generated from the RFMs of individual images, such that the entire strip of images can be treated as a single image. Correction parameters are calculated through bundle adjustments between strip images. For the experiment, we used two stereo strips. Each strip image consists of three KOMPSAT-3A scenes. Experimental results show that it was possible to improve the initial model by using the control points located in a specific region of the strip. We showed that absolute orientation with moderate accuracy of 2 m errors were achieved from 12 ground control points for the three-image strips. The test results indicate that bundle adjustment of strip images could be more efficient than bundle adjustments of the individual scenes.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.58-58
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• 2004

인공위성 편대비행에서는 위성간 거리가 수 미터에서 수 킬로미터에 달하기 때문에 궤도 배치 및 재배치시 위성간 충돌의 문제는 매우 중요하다. 따라서 궤도 배치 및 재배치 단계에서 위성간 충돌을 피하고, 연료소모를 최소화시키면서 목적한 최종 배치를 만족시키는 최적경로를 산출하는 방법이 최근들어 연구되고 있다. 최적 경로를 산출하는 궤적 최적화 (Trajectory optimization) 문제를 풀기 위한 방법으로 크게 직접적인 (Direct) 방법과 간접적인 (Indirect) 방법이 있다. (중략)

• ICROS
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• v.3 no.3
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• pp.29-35
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• 1997

본 논문에서는 인공위성의 자세를 측정하는 장치로서 태양센서, 지구수평센서, 자이로스코프, 별센서, 자장계 등의 자세감지장치와 궤도조정 및 자세제어를 하기 위한 모멘텀 휠, 반작용 휠, 가스 제트 추력기 등 각종 구동장치의 기술적 특성에 대해서 검토하고자 한다. 본 논문의 주목적은 최근 국내에서 활발히 추진되고 있는 인공위성 개발 사업 관련 위성체와 관련된 일반의 관심을 증대시키고 관련 실무 지식을 소개하고자 하는데 있다.

• Current Industrial and Technological Trends in Aerospace
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• v.7 no.1
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• pp.23-31
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• 2009

Insufficient problem about resource of satellite network frequency and orbit was seriously issued, because commercialization of a satellite has been successfully achieved since 1980s. Therefore, each countries execute an advantageous policy to them for guarantying and protecting satellite network resource and perform study for preoccupying new satellite network resource. Understanding and insight of policy about occupying satellite network resource of world each countries are landmark of satellite network task. In this paper, policies of Japan, Russia and China located around Korea are especially described. Also, in this paper, the administration organization of Japan, Russia and China which are to manage satellite network is described. The KARI(Korea Aerospace Research Institute) secured satellite network frequency and orbit of the KOMPSAT(KOrea Multi Purpose SATellite)-1 and the KOMPSAT-2 and is also going to register satellite network of the KOMPSAT-3 and the KOMPSAT-5. When satellite network coordination with nearby three countries will be needed, understanding of political policy and organization let the Korea acquire coordination agreement of the other administration.

• Journal of Astronomy and Space Sciences
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• v.18 no.2
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• pp.129-136
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• 2001

The accuracy of GPS applications is heavily dependent on the satellite ephemeris and earth orientation parameter. Specially applications like as the real time monitoring of troposphere and ionosphere require real time or predicted ephemeris arid earth orientation parameter with very high quality. IGS is producing IGS ultra rapid product called IGU for real time applications which includes the information of ephemeris and earth orientation. IGU is being made available twice everyday at 3:00 and 15:00 UTC arid covers 48 hours. The first 24 hours of it are based on actual GPS observations and the second 24 hours extrapolated. We will construct the processing strategy for yielding ultra rapid product and demonstrate the propriety through producing it using 48 hours data of 32 stations.

• Journal of Astronomy and Space Sciences
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• v.24 no.2
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• pp.145-154
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• 2007

Antenna pointing analysis for a geostationary satellite has been performed for using the NORAD Two-Line-Elements (TLE) converted from osculating Keplerian orbital elements. In order to check the possibility of the reception of the satellite signal, the antenna offset angles have been derived for the Communications, Ocean, and Meteorological Satellite (COMS) which carries out weekly East-West and North-South station-keeping maneuvers and twice a day thruster assisted momentum dumping. Throughout the analysis, it is shown that the use of converted NORAD TLE simplifies the antenna pointing related interfaces in satellite mission control system. For a highly eccentric transfer orbit cases, further analysis presents that the converted NORAD TLE from near apogee gives more favorable results.

• 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).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.426-430
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• 2005

The COMS(Communication, Ocean and Meteorological Satellite) is the first developed three-axis stabilization multi-function satellite on geostationary earth orbit(GEO) in korea, presently scheduled to be launched in 2008. The COMS propulsion system provides the thrust and torque required for the insertion into GEO, attitude and orbit control/adjustment of spacecraft. In this paper, system design of propulsion system, basic functions and design requirement of components are described.