• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.1
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• pp.39-47
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• 2005

In this paper, a method of station keeping strategy using relative orbital motion and numerical optimization technique is presented for geostationary spacecraft. Relative position vector with respect to an ideal geostationary orbit is generated using high precision orbit propagation, and compressed in terms of polynomial and trigonometric function. Then this relative orbit model is combined with optimization scheme to propose a very efficient and flexible method of station keeping planning. Proper selection of objective and constraint functions for optimization can yield a variety of station keeping methods improved over the classical ones. Results from the nonlinear simulation have been shown to support such concept.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.75-81
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• 2003

The longitude and latitude of a geosynchronous satellite are not defined as a point in space because of various external perturbations. To perform the missions of a satellite for a communication and broadcasting, the satellite must be positioned within a predefined station keeping box in given limited space longitude. In this study, we propose east-west station keeping box larger than that of north-south station. By using the derived error equation, we verified the Koreasat station keeping box allocation by assuming one week and two weeks of station keeping cycle.

• Journal of Astronomy and Space Sciences
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• v.23 no.3
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• pp.245-258
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• 2006

In this paper, an automation algorithm of analyzing and scheduling the station-keeping maneuver is presented for Communication, Ocean and Meteorological Satellite (COMS). The perturbation analysis for keeping the position of the geostationary satellite is performed by analytic methods. The east/west and north/south station-keeping maneuvers we simulated for COMS. Weekly east/west and biweekly north/south station-keeping maneuvers are investigated for a period of one year. Various station-keeping orbital parameters are analyzed. As the position of COMS is not yet decided at either $128.2^{\circ}E\;or\;116.0^{\circ}E$, both cases are simulated. For the case of $128.2^{\circ}E$, east/west station-keeping requires ${\Delta}V$ of 3.50m/s and north/south station-keeping requires ${\Delta}V$ of 52.71m/s for the year 2009. For the case of $116.0^{\circ}E,\;{\Delta}V$ of 3.86m/s and ${\Delta}V$ of 52.71m/s are required for east/west and north/south station-keeping, respectively. The results show that the station-keeping maneuver of COMS is more effective at $128.2^{\circ}E$.

• Bulletin of the Korean Space Science Society
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• 2005.04a
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• pp.58-58
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• 2005

• Journal of Satellite, Information and Communications
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• v.2 no.2
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• pp.16-21
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• 2007

Various perturbations by the sun, the moon and the earth itself cause a continuous change in nominal position of a geostationary satellite. In order to maintain the satellite within a required window, north-south station keeping for controlling inclination and right ascension of ascending node, and east-west station keeping for controlling eccentricity and longitude are required. In this paper, station keeping maneuver simulation for Communication, Ocean and Meteorological Satellite (COMS) was performed using COMS Flight Dynamics Software(FDS) and the results were analyzed. COMS performs weekly based east-west/north-south station keeping to maintain satellite within ${\pm}0.05^{\circ}$ at the nominal longitude of $128.2^{\circ}E$. In addition, COMS performs wheel off-loading maneuver twice a day to eliminate attitude error caused by one-solar wing in the south panel of the satellite. In this paper, station keeping maneuver considering wheel off-loading maneuver was performed and the results showed that COMS can be maintained well within ${\pm}0.05^{\circ}$ window using COMS FDS.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.64-74
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• 2003

This paper proposes a new autonomous stationkeeping system suitable for geostationary satellite and conducts computer simulation to verify the proposed algorithm. The proposed onboard system receives pseudo-range signal from ground equipments located at two different position with long baseline, determines the orbit error in realtime and generates orbit control commands. For minimized onboard stationkeeping logic and better reliability, the orbit controller is designed to generate control signal to have the orbit roughly follow predetermined reference range data which is generated through ground based computer simulation. The reference range data is assumed to be uploaded with time tag. A simple orbit controller is proposed which combines the reference $\Delta$V and feedback control signal. Finally, the performance of the proposed system is verified through the computer simulations.

• Proceedings of the Korean Information Science Society Conference
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• 2004.10b
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• pp.4-6
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• 2004

최근 이동체 관리 기술 중 물류 및 차량 관리, 응급 서비스 등 실세계에 많이 응용되는 도로 네트워크(도로, 철도 선로 등) 기반 이동체 관리에 대해 많은 연구가 진행되었다. 도로 네트워크를 따라 움직이는 이동체는 이동 영역이 한정되어 있기 때문에, 이러한 특징을 반영한 현재 위치 색인 및 과거 위치 색인이 개발되었다. 그러나 실세계 응용에서는 이동체의 과거 및 현재 위치를 모두 필요로 하는 경우가 많아서 두개의 색인을 별도로 유지하여야 하며, 이는 비효율적인 노드탐색 비용을 유발하고 색인 사이에 공통된 부분이 존재함에도 불구하고 중복된 유지를 해야 한다는 문제점이 있다. 본 논문에서는 이러한 문제점을 해결하기 위해 도로 네트워크 기반 이동체의 통합 색인을 제안한다 제안 색인은 도로 네트워크 기반 이동체의 현재 위치 색인 및 과거 위치 색인의 공통된 부분인 도로 네트워크를 저장.관리하는 부분을 공유하여 색인 유지비용을 줄이며, 현재 및 과거 위치 질의에 대해 불필요한 노드 탐색 비용도 감소시킨다. 또한 과거 및 현재 위치 색인을 통합함으로써 효율적으로 과거 위치 정보를 생성.저장하는 것이 가능해진다.

• Journal of Astronomy and Space Sciences
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• v.22 no.4
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• pp.527-536
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• 2005

The perturbations caused by the Sun and the Moon are predominantly out-of-plane effects causing a change in the inclination and in the right ascension of ascending node of a geostationary satellite. Due to the change of the inclination, subsatellite latitude of the geostationary satellite has a daily variations of the same magnitude of the inclination. Therefore we need a facility to control the orbital inclination and right ascension of ascending node for maintaining the satellite position in specified subsatellite latitude boundary using thrusters. In this paper we studied North-South station keeping strategies of the COMS-1 such as Track-Back Chord Target (TBCT) method, Maximum Compensation Target (MCT) method and Minimum Fuel Target (MFT) method. We accomplished those North-South station keeping maneuvers for one year starting from December 2008. The required velocity increments to maintain the satellite are estimated as MCT 52.6065m/s, TBCT 52.2383m/s, MFT 51.5428m/s, respectively. We demonstrated that TBCT and MFT methods are proper to North-South station keeping for COMS-1. MFT method showed the minimum required velocity increments whereas TBCT traced narrow inclination boundary area for North-South station keeping.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.67-76
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• 2004

This paper improves existing 'fly-the-wire' based autonomous station-keeping system, suitable for geostationary satellite and introduces results of computer simulations conducted to verify the algorithm. The on-board stationkeeping system receives pseudo-range signals from two ground equipments located with long baseline, determines the orbit error in realtime and generates orbit control commands. To reduce fuel consumption, this paper proposes an on-board orbit control logic using modified fly-the-wire method. The modified fly-the-wire method de-couples error components into two dynamic modes, harmonic and linear motion. The harmonic error components are removed by applying output commands produced by feedback controller, and the linear motions are controlled by the correction ${\Delta}V\;s$ added to reference maneuvers. The reference maneuvers are generated through the ground based computer simulation and embedded or uploaded into the on-board computer with time tags. Finally, the performance of the proposed algorithm is verified through a series of computer simulations.

• 한국공간정보시스템학회:학술대회논문집
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• 2005.11a
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• pp.161-167
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• 2005

RFID 태그 객체의 위치정보는 시간에 따라 궤적 정보가 누적되는 이동체와 유사한 특성을 가지지만 태그의 위치는 논리적인 리더의 위치로 인식되며 위치보고가 리더의 인식영역 안에서만 이루어지므로 시간축에 평행한 이산적인 시간간격 형태로 나타나는 차이점이 있다. 기존 이동체의 위치 추적 색인에서는 이동체의 위치를 연결된 다중선으로 표현하여 색인에 저장을 하기 때문에 시공간적으로 연결되지 않은 태그의 위치 정보를 저장하면 궤적 검색 비용이 매우 높아지는 문제가 발생한다. 이 논문에서는 이동체와는 다른 태그의 위치 특성을 반영하여 태그의 궤적 검색을 효율적으로 수행하는 색인 기법을 제안한다. 제안된 색인에서는 시간적으로 연결되지 않은 태그의 궤적 정보를 검색하기 위하여 동일 태그의 위치 간의 연결 정보를 유지하는 기법을 제시하고 있다. 또한, 부모 태그와 자식 태그간의 포함관계를 유지하는 기법을 제시함으로써 상품의 역학조사와 같이 물품에 부착된 태그간의 포함관계를 이용한 순방향 및 역방향 궤적 검색을 효율적으로 수행할 수 있도록 하고 있다.