• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.184-192
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• 2014

In this paper, the lifetime of the artificial space objects in the LEO is analysed by using TLE data, which is provided by JSpOC. We observed the change of the number of space objects from 1957 and determined the reason of space debris generation. And then, we performed the analysis about present condition of space debris environment. The lifetime analysis includes a total of 11,792 artificial space objects and performed until the year 2050 by orbit propagation. We analyze the annual reentry frequency for the high RCS objects such as nonoperational satellites and rocket bodies, which have the possibility of earth ground impact through STK/Lifetime Tool for accurate and effective calculation. The results show that 9 payloads or rocket bodies will be decayed annually and 2 or 3 objects of total value have the possibility of ground impact. In addition, it is also shown that the 40% of a total analysed objects have the lifetime over 200 years.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.43-52
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• 2004

In this paper, the performance of the KOMPSAT-1 orbit determination (OD) accuracy at the ground station was analyzed by using the flight data. The Bayesian least squares estimation was used for the orbit determination and the assessment of the orbit accuracy was evaluated based on orbit overlap comparisons. We also compared the result from OD using GPS navigation solutions with NORAD TLE and the result from OD using range data. Furthermore, the effect of observation type and OBT drift on the accuracy was investigated. As a consequence, It is shown that the OD accuracy using only GPS position data is on the order of 5m RMS (Root Mean Square) with 4 hrs arc overlap for the 30hr arc and the GPS velocity data is not proper as a observation for the OD due to its inferior quality. The significant deterioration of the accuracy due to the critical clock bias was not founded by means of the comparison of OD result from other observations.

• Physical Therapy Korea
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• v.25 no.4
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• pp.27-36
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• 2018

Background: We developed a novel integrative lumbar stabilization technique that combines lumbar extension (LE) exercise with abdominal drawing-in maneuver (ADIM) to ameliorate low back pain (LBP) associated with neuromuscular imbalance and instability, based on the collective evidence of contemporary spinal rehabilitation. Objects: The specific aim of the present study was to investigate the effects of LE exercise with and without ADIM on core muscle strength, lumbar spinal instability, and pain, as well as functional characteristics in individuals with LBP using advanced radiographic imaging techniques. Methods: patients with mechanical LBP (N = 40, 6 males; $35.1{\pm}7.6years$) were recruited and randomly assigned either to the combined LE and ADIM (experimental group) or the LE alone (control group). Outcome measures included the visual analog scale, the modified Oswestry Disability Index, muscle strength imbalance (MSI), and radiographic imaging. The lumbar intervertebral displacement (LID), intervertebral (IV) and total lumbar extension (TLE) angles were calculated to evaluate the lumbar segmental instability. Results: The experimental group showed significant differences in the L3-L4, L5-S1 LIDs, L4-L5 and L5-S1 IV angles, and TLE angle as compared to the controls (p<.05). Immediate pain reduction and muscle strength imbalance ratio were significantly different between the groups (p<.05). Conclusion: These results suggest that the addition of ADIM significantly increased lumbar spinal stabilization in individuals with LBP, thereby reducing pain associated with functional lumbar flexion during daily activities.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.5
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• pp.447-454
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• 2016

Increase of space debris makes low earth orbit(LEO) environment more complex day by day and space situation Awareness(SSA) is becoming more important. As an essential part of SSA, space object surveillance and tracking is studied by many countries including America and Europe. And radar system forms the backbone of an space surveillance and tracking. Currently, Korea operates many LEO satellites like KOMPSAT but does not have dedicated radar systems which provide collision surveillance between satellite and space debris. Korea Aerospace Research Institute(KARI) NARO space center operates launch-vehicle tracking radar system in GOHEUNG and JEJU, respectively. In this paper, we describe developing operation concept to track International Space Station(ISS) using NARO radar and results of tracking. Then, we describe ISS orbit determination using radar tracking data. Lastly, orbit determination result is compares with TLE for analyzing effectiveness of orbit determination.

• Proceedings of the Korea Water Resources Association Conference
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• 2022.05a
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• pp.439-439
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• 2022

인공위성은 위성통신, 기상 등 다양한 분야에서 활용되고 있지만 재난과 위성영상 특성 매칭의 제약으로 재난 상황에서는 제한적으로 사용되었다. 국내외 위성 갯수의 증가로 위성영상을 준-실시간으로 확보 가능함에 따라 활용할 수 있는 범위가 증가하여 최근에는 재난·재해에 신속하게 대비하기 위한 연구가 활발히 진행되고 있다. 본 연구는 재난 발생 지역의 위성 영상 확보를 위해 촬영된 영상과 미래시점의 촬영 예정인 영상의 촬영 예정 시간 및 영역을 빠른 시간 내 분석하여 최적 위성영상 확보에 기반이 되고자 한다. 행정안전부에서 분류한 재난·재해 유형에 따라 재난 예측, 탐지, 사후처리를 위한 위성자료의 확보를 위하여 다양한 위성과 탑재된 센서들의 궤도, 공간 해상도, 파장대 등의 위성영상의 적시성을 분석하여 최적 위성을 정의하였다. 위성 궤도 시뮬레이션은 TLE(Two Line Element) 정보를 이용하는 SGP4(Simplified General Perturbations version 4) 모델에 적용하여 개발하였다. 최신 TLE 정보를 이용하여 위성 궤도 정보 및 센서 정보(공간 해상도, Swath width, incidence angle IFOV 등)을 적용하였다. 수집된 위성 궤도 정보를 기반으로 위성의 궤도를 예측하여 예측된 위치에서의 촬영 영역을 산정하는 분석 기능을 수행하여 최종 시뮬레이션 데이터를 생성한다. 개발된 위성 궤도 시뮬레이션 알고리즘을 토대로 태풍 미탁 사례에 적용하였다. 위성 궤도 시뮬레이션 알고리즘을 태풍 미탁 사례에 적용한 결과 다종 위성리스트 중 위성 궤도 분석을 통해 최단기간 획득 가능한 위성 중 정지 궤도 기상위성인 Himawari-8, GK-2A는 태풍 경로 모니터링, 광학 위성인 Sentinel-2, PlanetScope는 건물 피해 지역, SAR 위성인 Sentinel-1, ICEYE는 홍수 지역을 탐지하는데 최적 위성 영상으로 분석되었다.

• The Korean Journal of Nuclear Medicine
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• v.35 no.1
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• pp.12-22
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• 2001

Purpose: The ictal perfusion patterns of cerebellum and basal ganglia have not been systematically investigated in patients with temporal lobe epilepsy (TLE). Their ictal perfusion patterns were analyzed in relation with temporal lobe and frontal lobe hyperperfusion during TLE seizures using SPECT subtraction. Materials and Methods: Thirty-three TLE patients had interictal and ictal SPECT, video-EEG monitoring, SPGR MRI, and SPECT subtraction with MRI co-registration. Results: The vermian cerebellar hyperperfusion (CH) was observed in 26 patients (78.8%) and hemispheric CH in 25 (75.8%). Compared to the side of epileptogenic temporal lobe, there were seven ipsilateral hemispheric CH (28.0%), fifteen contralateral hemispheric CH (60.0%) and three bilateral hemispheric CH (12.0%). CH was more frequently observed in patients with additional frontal hyperperfusion (14/15, 93.3%) than in patients without frontal hyperperfusion (11/18, 61.1%). The basal ganglia hyperperfusion (BGH) was seen in 11 of the 15 patients with frontotemporal hyperperfusion (73.3%) and 11 of the 18 with temporal hyperperfusion only (61.1%). In 17 patients with unilateral BGH, contralateral CH to the BGH was observed in 14 (82.5%) and ipsilateral CH to BGH in 2 (11.8%) and bilateral CH in 1 (5.9%). Conclusion: The cerebellar hyperperfusion and basal ganglia hyperperfusion during seizures of TLE can be contralateral, ipsilateral or bilateral to the seizure focus. The presence of additional frontal or basal ganglia hyperperfusion was more frequently associated with contralateral hemispheric CH to their sides. However, temporal lobe hyperperfusion appears to be related with both ipsilateral and contralateral hemispheric CH.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.49-49
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• 2003

2008년 발사 예정인 통신해양기상위성(Communication, Ocean and Meteorological Satellite)의 성공적인 임무완성에 기여하기 위해 본 연구에서는 해양위성 관측자료 분석에 적용할, 위성의 위치 및 하루 또는 연중 태양의 위치에 따른 해수면 태양반사(Sunglint) 영역의 정확한 위치를 찾아주는 예측 알고리즘을 연구하였다. 정지궤도위성의 태양반사 영역의 정확한 위치 결정은 태양-위성-지구를 고려한 구면 천문학과 반사의 법칙으로부터 계산할 수 있는데 적절한 구면 좌표계에서 하루 또는 연중 태양의 위치와 위성의 위치를 통해 얻어진 비선형 방정식을 Newton-Raphson 수치 방법을 이용하여 태양반사 영역의 정확한 위치와 움직임을 계산하였다. 또한 정지궤도위성이 아닌 극궤도위성의 태양반사 영역의 위치 결정은 해당 위성의 TLE(Two Line Elements)을 이용한 궤도분석 프로그램인 ASAP(Artificial Satellite Analysis Program)을 이용해 시간에 따른 위성의 위치를 구하여 정지궤도위성에서의 위치 결정 알고리즘과 같은 방식으로 연구를 수행하였다. 본 논문에서 연구한 기본적인 알고리즘을 통해 다양한 이미지 센서를 가진 궤도 위성에서의 태양반사 영역 위치 결정과 그와 관련된 연구를 수행 할 수 있을 것으로 기대한다.

• Journal of the Korean Institute of Intelligent Systems
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• v.7 no.2
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• pp.25-33
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• 1997

A DEDS is a system whose states change in response to the occurence of events from a predefined event set. In this paper, we consider the optimal control and reasoning problem for Discrete Event Systems(DES) in the Temporal Logic Framework(TEL) which have been recnetly defined. The TLE is enhanced with objective functions(event cost indices) and a measurement space is alos deined. A sequence of event which drive the system form a give initial state to a given final state is generated by minimizing a cost functioin index. Our research goal is the reasoning of optimal trajectory and the design of the optimal controller for DESs. This procedure could be guided by the heuristic search methods. For the heuristic search, we suggested the Stochastic Ruler algorithm, instead of the A algorithm with difficulties as following ; the uniqueness of solutions, the computational complexity and how to select a heuristic function. This SR algorithm is used for solving the optimal problem. An example is shown to illustrate our results.

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.304-307
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• 2004

Satellite orbit determination using angles only data from single ground station is carried out. The KOMPSAT-1 satellite mono-pulse angle tracking data from 9-meter S-band antenna at KARI site in Daejeon are used for the orbit determination. Various angle tracking arcs from one-day to five-day are processed and the orbit determination results are analyzed. Antenna pointing data are predicted based on the orbit determination results to check the possibility of re-acquisition and tracking of the satellite signal. Normal satellite mission operations including orbit determination, antenna prediction, satellite re-acquisition and automatic tracking from predicted antenna angle pointing data are concluded to be possible when three-day angle tracking data from single tracking station are used for the orbit determination.

• Journal of Astronomy and Space Sciences
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• v.36 no.3
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• pp.169-180
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• 2019

In this study, a batch least square estimator that utilizes optical observation data is developed and utilized to determine geostationary orbits (GEO). Through numerical simulations, the effects of error sources, such as clock errors, measurement noise, and the a priori state error, are analyzed. The actual optical tracking data of a GEO satellite, the Communication, Ocean and Meteorological Satellite (COMS), provided by the optical wide-field patrol network (OWL-Net) is used with the developed batch filter for orbit determination. The accuracy of the determined orbit is evaluated by comparison with two-line elements (TLE) and confirmed as proper for the continuous monitoring of GEO objects. Also, the measurement residuals are converged to several arcseconds, corresponding to the OWL-Net performance. Based on these analyses, it is verified that the independent operation of electro-optic space surveillance systems is possible, and the ephemerides of space objects can be obtained.