• International Journal of Aeronautical and Space Sciences
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• 제6권1호
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• pp.71-76
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• 2005

The KOMPSAT-1 satellite, launched into a circular sun synchronous orbit on Dec. 21, 1999, entered its$6^{th}$year of successful operation this year. The purposes of the mission are to collect earth images (6.6 m resolution), multi-spectral images of the ocean, and to collect information on the particle environment of the low earth orbit. For normal operation, KOMPSAT-1 orbits are determined using GPS navigation solutions. However, at the start of the life of KOMPSAT-1, the 11-year solar activity cycle was at a maximum. Solar flux was maintained at this level until 2002, and thereafter reduced to a moderate level by 2004. Thus, the OD (Orbit Determination) accuracy has varied according to the solar activity. This paper presents the degree to which the OD accuracy could be degraded during a high solar activity period compared with that of a (relatively) low solar activity period. We investigated the effect of the use of solve-for parameters such as a drag coefficient ($C_D$), solar radiation coefficient ($C_R$), and the general accelerations ($G_A$) on OD accuracy with solar activity. For the evaluation of orbit determination accuracy, orbit overlap comparison is used since no independent orbits of comparable accuracy are available for comparison. The effect of the use of a box-wing model instead of a constant cross-sectional area is also investigated.

• Journal of Astronomy and Space Sciences
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• 제37권4호
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• pp.237-247
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• 2020

The ground tracking support is a critical factor for the navigation performance of spacecraft orbiting around the Moon. Because of the tracking limit of antennas, only a small number of facilities can support lunar missions. Therefore, case studies for various ground tracking support conditions are needed for lunar missions on the stage of preliminary mission analysis. This study analyzes the ground supporting condition effect on orbit determination (OD) of Korea Pathfinder Lunar Orbiter (KPLO) in the lunar orbit. For the assumption of ground support conditions, daily tracking frequency, cut-off angle for low elevation, tracking measurement accuracy, and tracking failure situations were considered. Two antennas of deep space network (DSN) and Korea Deep Space Antenna (KDSA) are utilized for various tracking conditions configuration. For the investigation of the daily tracking frequency effect, three cases (full support, DSN 4 pass/day and KDSA 4 pass/day, and DSN 2 pass/day and KDSA 2 pass/day) are prepared. For the elevation cut-off angle effect, two situations, which are 5 deg and 10 deg, are assumed. Three cases (0%, 30%, and 50% of degradation) were considered for the tracking measurement accuracy effect. Three cases such as no missing, 1-day KDSA missing, and 2-day KDSA missing are assumed for tracking failure effect. For OD, a sequential estimation algorithm was used, and for the OD performance evaluation, position uncertainty, position differences between true and estimated orbits, and orbit overlap precision according to various ground supporting conditions were investigated. Orbit prediction accuracy variations due to ground tracking conditions were also demonstrated. This study provides a guideline for selecting ground tracking support levels and preparing a backup plan for the KPLO lunar mission phase.

• Maxillofacial Plastic and Reconstructive Surgery
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• 제28권3호
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• pp.222-228
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• 2006

Various methods have been used in the past to indirectly analyze the craniofacial region. Among these, the lateral and posterior-anterior cephalometircs are used for the evaluation of the dentofacial deformities. However, cephalometircs create inaccuracies because of the inherent enlargement and distortion of the image. The interpretation of cephalometric films is also problematic: the number of anatomic landmarks that can be identified accurately is limited, and the overlap of structures on a radiograph making locating these landmarks difficult. To overcome these problems, computed tomography(CT) has been recommended as an useful modality in the diagnosis, surgical planning, and follow-up of craniofacial anomalies. There is no significant enlargement or distortion of the image, overlap of structure, or tracing error. And the number of anatomic landmarks is vast. The purpose of this study was to examine the orbit and midfacial region using Occlusal Maxillary CT, consisted of slices parallel to the occlusal plane. Based on these CT scan, we provide the data that could be applied to monitor an individual patient's skeletal pattern and the guide to the maxillary osteotomy.

• Journal of Astronomy and Space Sciences
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• 제28권4호
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• pp.299-304
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• 2011

As more satellites are designed to downlink their observed image data through the X-band frequency band, it is inevitable that the occupied bandwidth of a target satellite will overlap with that of other X-band downlink satellites. For sun-synchronized low earth orbit satellites, in particular, it can be expected that two or more satellites be placed within the looking angle of a ground station antenna at the same time. Due to the overlapping in the frequency band, signals transmitted from the adjacent satellites act as interferers, leading to degraded link performance between target satellite and ground station. In this paper, link analysis was initiated by modeling the radiation pattern of ground station antenna through a validated Jet Propulsion Laboratory peak envelope model. From the relative antenna gain depending on the offset angle from center axis of maximum antenna directivity, the ratio of received interference signal level to the target signal level was calculated. As a result, it was found that the degradation increased when the offset angle was within the first point of radiation pattern. For a 7.3 m antenna, serious link degradation began at an offset angle of 0.4 degrees. From this analysis, the link performance of the coming satellite passes can be recognized, which is helpful to establish an operating procedure that will prevent the ground station from receiving corrupted image data in the event of a degraded link.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.182-185
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• 2005

Satellite cameras are calibrated before launch in detail and in general, but it cannot be guaranteed that the geometry is not changing during launch and caused by thermal influence of the sun in the orbit. Modem satellite imaging systems are based on CCD-line sensors. Because of the required high sampling rate the length of used CCD-lines is limited. For reaching a sufficient swath width, some CCD-lines are combined to a longer virtual CCD-line. The images generated by the individual CCD-lines do overlap slightly and so they can be shifted in x- and y-direction in relation to a chosen reference image just based on tie points. For the alignment and difference in scale, control points are required. The resulting virtual image has only negligible errors in areas with very large difference in height caused by the difference in the location of the projection centers. Color images can be related to the joint panchromatic scenes just based on tie points. Pan-sharpened images may show only small color shifts in very mountainous areas and for moving objects. The direct sensor orientation has to be calibrated based on control points. Discrepancies in horizontal shift can only be separated from attitude discrepancies with a good three-dimensional control point distribution. For such a calibration a program based on geometric reconstruction of the sensor orientation is required. The approximations by 3D-affine transformation or direct linear transformation (DL n cannot be used. These methods do have also disadvantages for standard sensor orientation. The image orientation by geometric reconstruction can be improved by self calibration with additional parameters for the analysis and compensation of remaining systematic effects for example caused by a not linear CCD-line. The determined sensor geometry can be used for the generation? of rational polynomial coefficients, describing the sensor geometry by relations of polynomials of the ground coordinates X, Y and Z.

• 대한원격탐사학회지
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• 제34권6_1호
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• pp.1143-1153
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• 2018

TOPS InSAR 처리를 위해서는 고정밀도의 영상정합이 요구된다. Sentinel-1 TOPS 모드영상에 교차상관 영상정합, 기하정합, Spectral Diversity 정합에 기반 한 Enhanced Spectral Diversity 정합 알고리즘 성능 비교분석을 통해 TOPS모드에 적합한 영상정합 방법을 제시하고자 한다. 25개의 Sentinel-1 TOPS 영상으로부터 생성된 23개의 간섭쌍을 이용하여, 교차상관정합(CC), 기하보정(GC1), 기하보정 후 교차상관정합(GC2, GC3, GC4) 그리고 ESD를 이용한 정합(ESD_GC, ESD_1, ESD_2) 총 8가지 방법을 적용하였다. 교차상관정합과 기하정합에 따른 azimuth 방향 정합오차를 평균한 결과는 각각 0.0041 화소, 0.0016 화소이다. 비록 ESD 방법은 azimuth 정합오차가 0.0005 화소 이하로 가장 정확한 결과를 보이지만, 기하정합 결과는 추가적인 교차상관정합을 통한 반복 과정을 통해 0.001 화소 정도로 오차가 감소하였다. ESD 방법은 burst 중첩지역의 긴밀도가 낮은 경우 적용이 불가능하다. 따라서 반복 적용을 통한 기하정합 방법은 다수의 SAR 자료를 이용한 시계열 분석 또는 긴 시간간격을 갖는 간섭도 생성을 위해서 적합한 대안이 된다.

• 대한원격탐사학회지
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• 제28권1호
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• pp.69-77
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• 2012

표면도달일사량은 전 지구시스템에 대한 기후 연구에 가장 중요한 요소 중 하나다. 기후 연구에서는 동일 지역을 관측하는 두 개 혹은 그 이상의 위성자료로부터 넓은 공간적 범위를 가지는 장기간의 데이터를 사용하는 것이 필요하다. 시간적 연속성을 가지는 서로 다른 위성으로부터 산출 된 표면도달일사량의 연속성과 일관성을 향상시키는 것은 매우 중요하다. 본 연구에서는 물리적 모델을 이용하여 GOES-9과 MTSAT-1R 위성의 중복 관측 기간 동안의 표면도달일사량을 산출하고, 두 위성의 채널자료와 실측치 비교를 통해 위성간의 연속성과 일관성을 향상시키는 방법을 연구하였다. 두 위성의 적외 채널 온도는 매우 잘 일치하는 경향을 보였다 : RMSE=5.595 Kelvin; Bias=2.065 Kelvin. 반면에, 가시채널은 다른 값의 분포를 보였지만 비슷한 경향을 보였다. 그리고 두 위성으로부터 산출 된 표면도달일사량은 실측치와 일치성이 낮았다. 표면도달일사량의 품질 향상을 위해 구름감쇠계수 조정을 통해 표면도달일사량 산출물을 재생산하였다. 그리고 채널 자료의 비교 분석을 통해 GOES-9 위성을 위한 구름감쇠계수를 생산하였다. 그 결과, 구름 효과를 고려한 GOES-9의 표면도달일사량 산출물은 MTSAT-1R과 실측치에 대해 매우 높은 일치성을 보였다 : RMSE=$83.439W\;m^{-2}$; Bias=$27.296W\;m^{-2}$. 구름감쇠계수 조정을 통해 향상 된 정확도는 두 개 이상의 위성으로부터 산출 된 표면도달일사량 산출물의 연속성과 일관성을 향상 시킬 수 있을 것이다.