• Journal of Astronomy and Space Sciences
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• v.15 no.2
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• pp.427-436
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• 1998

The apogee manoeuvre of $KOREASAT-1{cdot}2{cdot}3$ is basic elliptical orbit transfer converting orbit plane. The KOREASAT-3 is planed for multi-burn manoeuvres using the liquid apogee engine while the $KOREASAT-1{cdot}2$ used the apogee kick motor that executes a single burn in the apogee of transfer orbit using the solid propellant. This study analyzed the multi-burn manoeuvres using the liquid apogee engine and the propellant control method and developed the simulation tools. For the purpose of precise simulation, We designed tools in the basic of orbit propagation software, COWELL5, that was developed by members of Center for Astrodynamics in Yonsei university and the results can be displayed in 3-D graphic of $STK/VO^{TM}$.

• The Korean Publising Journal, Monthly
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• s.116
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• pp.6-7
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• 1992

• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.96-107
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• 2014

Korea Aerospace Research Institute has a plan to launch experimental lunar orbiter in 2017, and lunar orbiter and lander in 2020. In the mission planning phase, LOI(Lunar Orbit Insertion) maneuver strategy should be designed using finite burn model because on-board propulsion system of lunar orbiter in finite burn type. LOI maneuver plan and amount of required ${\Delta}V$ using finite burn model depend on the spacecraft attitude at burn, a type of propellant, thrust level and burn timing. This paper describes the LOI maneuver of lunar orbiter of foreign space agency and then comes up with the LOI maneuver plan of Korean lunar orbiter. Adequate thrust level and burn duration of Korean lunar orbiter also present by performing simulation.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.24.3-24.3
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• 2011

우주발사체를 이용하여 인공위성을 궤도에 올리는 문제에서 가장 중요시해야 할 부분은 임무의 성공, 즉 정밀한 궤도 진입이다. 이것이 만족되어졌을 때, 비용의 최소화 또한 설계 시 중요한 고려사항이 된다. 이 두 가지 문제를 동시에 해결하기 위해선 최적 제어 전략이 필요한데, 통상적으로 이 과정은 발사 전에 최적화 기법 등을 이용하여 계산되고 검증된다. 그러나 기존의 최적화 기법은 대부분 선형 시스템에 적합한 기법들 이고, 우주발사체와 같이 매우 복잡하고 강한 비선형을 가진 운동방정식을 최적화 하려면 많은 계산이 소요된다. 계산 소모 시간을 줄이기 위해서는 선형화 등의 기법이 사용되는데, 그러한 경우 최적 해에 대한 신뢰도가 낮아질 수밖에 없다. 이 논문에서는 그러한 문제를 해결하기 위해 최근 활발히 연구되고 있는 비선형 최적화 기법인 상태 의존 Riccati 방정식 기법 (SDRE)을 이용하여 인공위성을 주어진 궤도에 진입시키는 우주발사체의 최적궤도를 계산하였다. 또한 Hamiltonian 을 이용하여 산출된 궤도의 최적성을 보이고, 목표한 궤도와의 비교를 통해 제어기의 정밀성을 확인하였다.

• Journal of Aerospace System Engineering
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• v.10 no.4
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• pp.90-97
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• 2016

GEO-KOMPSAT-2A and GEO-KOMPSAT-2B are under development by KARI to replace the COMS mission, and will be launched in 2018 and 2019, respectively. GEO-KOMPSAT-2 will be launched and injected into the GTO (Geostationary Transfer Orbit) by the Ariane V launcher. Once injected into the GTO, the satellites are transferred to the drift orbit by applying a series of apogee engine burns. The burn epoch time, duration, and intervals are selected such that the satellite is placed closest to the target drift longitude, or at the drift start longitude. For GEO-KOMPSAT-2, four or five LAE (Liquid Apogee Engine) burns will be applied for drift orbit injection. This paper establishes the GEO-KOMPSAT-2 LAE burn plan, considering predefined constraints and adjustments, taking into account the perturbing forces. Two approaches have been analyzed: the first is a single shot approach, whereas the other is an iteration based optimal solution. Optimal solution has been obtained using the Focusleop, a geostationary satellite LEOP tool.

• ICROS
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• v.3 no.2
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• pp.41-50
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• 1997

본 논문에서는 무궁화위성의 발사단계에서부터 궤도상 운용에 이르기까지 각 임무 단계별로 필요한 궤도제어 기법을 살펴보았다. 정지궤도 통신/방송 위성은 정지궤도 진입 및 정지궤도상에서 임무 수행을 위한 정밀 궤도 제어 등 궤도제어와 관련하여 궤도 결정과 함께 지상국용 임무설계 S/W를 필요로 한다. 정지궤도 위성의 이러한 궤도 제어 기술은 향후 국내의 자체 정지궤도 위성 개발시 관련 기술의 국산화에 많은 도움이 될 것으로 기대된다. 또한 현재 무궁화위성 1, 2호의 운용기술을 자체 습득하고 고도화하는 노력도 향후 계속되는 국내 수요에 대비하여 계속되어야 할 것이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.207-210
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• 2011

Chollian bipropellant propulsion system is composed of one main engine for orbit transfer and fourteen thrusters for on-station operations. The design and analyses of the propulsion system were carried out in the framework of international collaboration. Following the system integration and testings required, the Chollian was transported to Kourou Space Center in French Guiana and launched successfully. After it separated from the launcher, the propulsion system was initialised automatically. Then three times of main engine firing were successfully performed, and the target obit insertion was accomplished.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.2
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• pp.156-165
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• 2015

A survivability-analysis program has been developed to analyze the ground collision risk of atmospheric reentry objects, such the upper stages of a launch vehicle or satellites, which move at or near the orbital velocity. The aero-thermodynamic load during the free fall, the temperature variation due to thermal load, and the phase shift after reaching the melting point are integrated into the 3 degree-of-freedom trajectory simulation of the reentry objects to analyze the size and weight of its debris impacting the ground. The analysis results of the present method for simple-shaped objects are compared with the data predicted by similar codes developed by NASA and ESA. Also, the analysis for actual reentry orbital objects has been performed, of which results are compared with the measurement data.

• Journal of Astronomy and Space Sciences
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• v.7 no.1
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• pp.37-45
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• 1990

It was investigated that the effect of zonal harmonics to transfer orbit. Since parking orbit is located at low altitude, the zonal harmonics affects transfer orbit relatively high sense. So under the zonal harmonics, eccentricity and semi-major-axis which were related orbit altitude at the first hand, were investigated. As a result the zonal harmonics increases the altitude of apogee of transfer orbit. So if the zonal harmonics is considered in orbit transfer the fuel can be saved a little.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.122-130
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• 2014

GEO-KOMPSAT-2 which is under development by KARI to be launched in 2018 is expected to be injected into its orbit through the standard GTO(Geostationary Transfer Orbit) or SSTO(Supersynchronous Transfer Orbit). While the standard GTO mission has been applied for the most of the geostationary satellites, the SSTO mission is rare case and significantly different from the standard GTO mission in technical point of view. This paper lists the operational constraints to be applied for GEO-KOMPSAT-2 SSTO mission, and introduces a preliminary LAE burn plan for GEO-KOMPSAT-2 mission. In order to evaluate the developed plan, a simulation study has been performed considering ground station visibility.