• Journal of Astronomy and Space Sciences
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• v.15 no.1
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• pp.235-244
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• 1998

The solutions of orbital maneuver problem using the sliding mode control in the presence of the erath gravitational perturbations is obtained. Especially, the optimization of consuming fuel for maneuver is performed. The impulsive solution to Lambert's problem using the combined equation method to minimize total ${\Delta}V is used for the desired orbit and the maneuver times. Two-step sliding mode control method is introduced for satisfying the boundary conditions of finite-thrust rendezvous problem at the end of maneuver time. Using the new approach to the orbit maneuver problem, two-step sliding mode control, orbit maneuvers are processed. The solutions to a rendezvous using the optimal control are obtained, and they are compared to the results by two-step sliding control.According to the new approach for orbit maneuver, the thrust-coast-thrust type controller is obtained to make satellite to track desired Lambert's orbit, and the total ${\Delta}V$ required for maneuver is resonable in comparison with the impulsive solution to Lambert's problem. The final state variables, also are close to the boundary conditions at the end of maneuver times.

• Proceedings of the KSRS Conference
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• 2000.04a
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• pp.1-1
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• 2000

아리랑위성 1호는 1999년 12월 21일 미국 캘리포니아 반덴버그 공군기지에서 성공적으로 발사되어 초기 고도 702.5km, 궤도경사각 98.26도의 궤도 진입에 성공하였다. 발사 후 2 개월간의 초기 운용기간 (Launch Early Operation Phase) 동안 위성체의 점검 및 기본 기능시험이 완료되었고 현재 위성은 정상 임무궤도에서 운용되고 있다. 초기 운용기간에 위성에 탑재된 관측센서의 기능분석 및 시험 영상 촬영도 이루어졌다. 본 발표에서는 초기 운용기간에 전자광학카메라 (EOC)와 해석관측센서 (OSMI)로부터 획득한 영상자료의 일부를 공개한다. 이를 통해 향후 국토이용관리, 해양 및 기상 등 다 방면에 활용될 EOC 및 OSMI 자료의 현재 수신상황을 설명하고 영상자료에 대한 이해를 도모하고자 한다.

• Bulletin of the Korean Space Science Society
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• 1998.10a
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• pp.43.2-43
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• 1998

• Information and Communications Magazine
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• v.17 no.1
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• pp.71-80
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• 2000

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.59-59
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• 2004

최근에 발사되어 임무를 수행중인 GRACE(Gravity Recovery And Climate Experiment) 위성사업은 편대비행하는 두 개의 저궤도 위성 간 거리를 측정하여 지구중력장을 관측하는 연구인데, 여기에 사용되는 위성간 거리측정기 성능분석을 위한 기본연구단계로, 해석식을 이용하여 외력과 위성간 거리변화와의 관계를 연구하였다. 원궤도에 근접한 궤도를 비행하는 위성의 운동은 Hill's 방정식을 사용하여 나타낼 수 있는데, 이로부터 위성에 가해지는 외력에 의한 위성의 운동 관계식을 얻을 수 있다. (중략)

• Atmosphere
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• v.12 no.4
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• pp.10-19
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• 2002

독자적 위성통신 기술 개발, 기상재난 조기예측체계 구축 및 해양관측을 위해 국내최초로 제작될 정지궤도 위성인 통신해양기상위성은 집중호우, 태풍, 황사, 적조로 인한 피해를 최소화하여 대국민 복지를 제고하고 국가재난 안전관리 체계 구축 및 남북통일에 대비한 신속한 위성통신망 구축을 목적으로 하고 있다. 통신해양기상 위성 개발 사업은 2003년에 본사업에 착수하고 2008년에 발사할 예정이며 과학기술부, 정보통신부, 해양수산부, 기상청의 주관으로 한국항공우주연구원, 한국전자통신연구원, 해양연구원, 기상연구소 및 국내 관련산업체 등이 개발에 참여하게 된다. 정지궤도위성의 국내개발을 통해 외화절감 및 수입대체효과를 가져오고, 통신해양기상위성 독자개발국으로서의 대외적 위상을 제고할 것이다.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.193-200
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• 2011

The external disturbance torque acting on a low earth orbit spacecraft was analyzed. For the Earth pointing attitude, the maximum torque to the spacecraft is about $8.3{\times}10^{-4}$ Nms and the momentum accumulated for an orbit is about 1.4 Nms and for the Sun pointing attitude, the maximum torque to the spacecraft is about $1.6{\times}10^{-3}$ Nms and the momentum is accumulated about 3.0 Nms in the spacecraft body reference frame. The analysis results confirm that the size of magnetic torquer selected previously for the satellite is sufficient to manage the accumulated momentum by considering the dumping capacity for an orbit.

• Journal of Astronomy and Space Sciences
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• v.7 no.1
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• pp.23-35
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• 1990

Resonance effect on the orbital elements of geosynchronous artificial satellite due to the non-zonal geopotential has been calculated. For the perturbation of a artificial satellite, perturbation effects due to the non-zonal geopotential is less than due to the $J_2$ or Luni-Solar perturbation, but non-zonal harmonics resonance exist. So, we calculate the perturbation of geosynchronous artificial satellite orbit due to the non-zonal harmonics resonance. The effect on the orbit eccentricity of non-zonal harmonics resonance is represented by a phase plane plot of ec. The effect on the orbit eccentricity of non-zonal harmonics resonance is represented by a phase plane plot of $e_c$ verse $e_s$. The evolution of mean longitude and semi-major axis are obtained.

• 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.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.27 no.5
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• pp.529-534
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• 2009

In this study, we investigate the feasibility of modeling entire image strips that has been acquired from the same orbital segments. We tested sensor models based on satellite orbit and attitude with different sets(Type1 ~ Type4) of unknowns. We checked the accuracy of orbit modeling by establishing sensor models of one scene using control points extracted from the scene and by applying the models to adjacent scenes within the same orbital segments. Results indicated that modeling of individual scenes with 1st or 2nd order unknowns was recommended. We tested the accuracy of around control points, digital map using the HIST-DPW (Hanjin Information Systems & Telecommunication Digital Photogrammetric Workstation) As a result, we showed that the orbit-based sensor model is a suitable sensor model for making 1/25,000 digital map.