• 한국전자파학회논문지
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• 제25권2호
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• pp.208-216
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• 2014

달 탐사 미션 수행을 위한 지상국은 달 궤도선과 착륙선의 상태 정보 및 관측한 센서 데이터를 수신할 수 있어야 한다. 이러한 지상 시스템 개발 초기 단계에서는 정확한 링크 파라미터에 의한 링크 분석을 통해 지상 안테나의 크기 및 시스템 잡음 성능이 도출되어야 한다. 한편, 지상 안테나가 달 궤도선과 착륙선과 통신을 할 경우에 달을 지향하게 되고, 이 때 달은 자체 밝기에 의해 안테나의 수신 성능을 열화 시키는 잡음으로써 동작한다. 본 논문에서는 안테나가 달을 지향할 때 발생되는 수신 성능 열화에 대한 분석 결과를 제시한다. 결과 검증을 위해 달에 의한 안테나 잡음 온도를 우선 계산 한 후에 이를 본 논문에서 제안하는 시험 방식의 결과와 비교하였고, 그 결과는 허용 오차 수준에서 일치함을 확인하였다. 이는 달에 의한 안테나 잡음 온도의 계산 방식이 정당함을 검증한 것이므로 이 방식을 통하여 다양한 주파수와 안테나의 크기에 따른 달 탐사 지상 안테나의 수신 열화 분석을 수행할 수 있었다.

• Journal of Astronomy and Space Sciences
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• 제38권3호
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• pp.185-192
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• 2021

This technical paper deals the practical transformation algorithms between several lunar reference frames which will be used for Korea pathfinder lunar orbiter (KPLO) flight operation. Despite of various lunar reference frame definitions already exist, use of a common transformation algorithm while establishing lunar reference frame is very important for all members related to KPLO mission. This is because use of slight different parameters during frame transformation may result significant misleading while reprocessing data based on KPLO flight dynamics. Therefore, details of practical transformation algorithms for the KPLO mission specific lunar reference frames is presented with step by step implementation procedures. Examples of transformation results are also presented to support KPLO flight dynamics data user community which is expected to give practical guidelines while post processing the data as their needs. With this technical paper, common understandings of reference frames that will be used throughout not only the KPLO flight operation but also science data reprocessing can be established. It is expected to eliminate, or at least minimize, unnecessary confusion among all of the KPLO mission members including: Korea Aerospace Research Institute (KARI), National Aeronautics and Space Administration (NASA) as well as other organizations participating in KPLO payload development and operation, or further lunar science community world-wide who are interested in KPLO science data post processing.

• 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.

• 우주기술과 응용
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• 제1권1호
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• pp.49-63
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• 2021

태양계 천체 탐사는 다양한 탑재체를 통해 이루어지고 있고, 그에 따라 많은 연구 결과들이 나오고 있다. 우리는 태양계 천체 연구의 한 방법으로 딥러닝 적용을 시도해 보았다. 지구 관측 위성 자료와 다르게 태양계 천체 자료들은 천체들에 따라 탐사선에 따라 각 탐사선의 탑재체에 따라 그 자료의 형태가 매우 다르다. 그래서 학습시킨 모델로 다양한 자료에 적용이 어려울 수 있지만 사람에 의한 오류를 줄이거나, 놓치는 부분들을 보완해 줄 수 있을 것이라고 기대한다. 우리는 달 표면의 크레이터를 탐지하는 모델을 구현해 보았다. Lunar Reconnaissance Orbiter Camera (LROC) 영상과 제공하는 shapefile을 입력값으로 하여 모델을 만들었고, 이를 달 표면 영상에 적용하여 보았다. 결과가 만족스럽지는 못했지만 이후 이미지 전처리와 모델 수정 작업을 통해 최종적으로는 ShadowCam에 의해 획득되는 달의 영구음영지역 영상에 적용할 예정이다. 이 외에도 달 표면과 비슷한 형태를 가진 세레스와 수성에 적용을 시도하여 딥러닝이 태양계 천체 연구에 또 다른 방법임을 시사하고자 한다.

• Journal of Astronomy and Space Sciences
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• 제40권2호
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• pp.79-88
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• 2023

On Aug. 4, 2022, at 23:08:48 (UTC), the Korea Pathfinder Lunar Orbiter (KPLO), also known as Danuri, was launched using a SpaceX Falcon 9 launch vehicle. Currently, KPLO is successfully conducting its science mission around the Moon. The National Aeronautics and Space Administration (NASA)'s Deep Space Network (DSN) was utilized for the successful flight operation of KPLO. A great deal of joint effort was made between the Korea Aerospace Research Institute (KARI) and NASA DSN team since the beginning of KPLO ground system design for the success of the mission. The efficient utilization and management of NASA DSN in deep space exploration are critical not only for the spacecraft's telemetry and command but also for tracking the flight dynamics (FD) operation. In this work, the top-level DSN interface architecture, detailed workflows, DSN support levels, and practical lessons learned from the joint team's efforts are presented for KPLO's successful FD operation. Due to the significant joint team's efforts, KPLO is currently performing its mission smoothly in the lunar mission orbit. Through KPLO cooperative operation experience with DSN, a more reliable and efficient partnership is expected not only for Korea's own deep space exploration mission but also for the KARI-NASA DSN joint support on other deep space missions in the future.

• Journal of Astronomy and Space Sciences
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• 제40권4호
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• pp.199-215
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• 2023

The Korea Pathfinder Lunar Orbiter (KPLO), the first South Korea lunar exploration probe, successfully arrived at the Moon on December, 2022 (UTC), following a 4.5-month ballistic lunar transfer (BLT) trajectory. Since the launch (4 August, 2022), the KPLO magnetometer (KMAG) has carried out various observations during the trans-lunar cruise phase and a 100 km altitude lunar polar orbit. KMAG consists of three fluxgate magnetometers capable of measuring magnetic fields within a ± 1,000 nT range with a resolution of 0.2 nT. The sampling rate is 10 Hz. During the originally planned lifetime of one year, KMAG has been operating successfully while performing observations of lunar crustal magnetic fields, magnetic fields induced in the lunar interior, and various solar wind events. The calibration and offset processes were performed during the TLC phase. In addition, reliabilities of the KMAG lunar magnetic field observations have been verified by comparing them with the surface vector mapping (SVM) data. If the KPLO's mission orbit during the extended mission phase is close enough to the lunar surface, KMAG will contribute to updating the lunar surface magnetic field map and will provide insights into the lunar interior structure and lunar space environment.

• 대한설비공학회:학술대회논문집
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• 대한설비공학회 2004년도 하계학술발표 논문집
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• pp.138-138
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• 2004

• Journal of Astronomy and Space Sciences
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• 제34권3호
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• pp.213-223
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• 2017

The deep space orbit determination software (DSODS) is a part of a flight dynamic subsystem (FDS) for the Korean Pathfinder Lunar Orbiter (KPLO), a lunar exploration mission expected to launch after 2018. The DSODS consists of several sub modules, of which the orbit determination (OD) module employs a weighted least squares algorithm for estimating the parameters related to the motion and the tracking system of the spacecraft, and subroutines for performance improvement and detailed analysis of the orbit solution. In this research, DSODS is demonstrated and validated at lunar orbit at an altitude of 100 km using actual Lunar Prospector tracking data. A set of a priori states are generated, and the robustness of DSODS to the a priori error is confirmed by the NASA planetary data system (PDS) orbit solutions. Furthermore, the accuracy of the orbit solutions is determined by solution comparison and overlap analysis as about tens of meters. Through these analyses, the ability of the DSODS to provide proper orbit solutions for the KPLO are proved.

• 한국결정성장학회지
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• 제5권4호
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• pp.370-377
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• 1995

우주 항공 기술의 첨단인 Space Shuttle Orbiter(SSO)의 두 coating material 인 Reaction Cured Glass(RCG)와 Spinel(C742)을 제조하여, 표면 위에 부딪히는 원자들의 재결합 가능성 $\gamma$를 확산반응기에서 측정하였다. SSO의 재진입 온도인 약 1000K에서 C742의 산소 원자들의 재결합 가능성 $\gamma$는 $3 {\times} 10^{-2}$으로 RCG에서의 $4 {\times} 10^{-4}$ 보다는 더 큰 값을 갖는다. C742에서 $\gamma$값이 더 높다는 것은 RCG에서 보다 더 많은 활성점을 갖고 있다는 것을 의미한다. 낮은 온도에서 활성점에 있는 원자의 탈착을 유도함으로써 보다 활성이 낮은 표면 코팅 재료를 개발할 수 있다.

• Journal of Astronomy and Space Sciences
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• 제20권1호
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• pp.1-10
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• 2003

A precise kinematic orbit determination (P-KOD) procedure for Low Earth Orbiter(LEO) using the GPS ion-free triple differenced carrier phases is presented. Because the triple differenced observables provide only relative information, the first epoch's positions of the orbit should be held fixed. Then, both forward and backward filtering was executed to mitigate the effect of biases of the first epoch's position. p-KOD utilizes the precise GPS orbits and ground stations data from International GPS Service (IGS) so that the only unknown parameters to be solved are positions of the satellite at each epoch. Currently, the 3-D accuracy off-KOD applied to CHAMP (CHAllenging Min-isatellite Payload) shows better than 35 cm compared to the published rapid scientific orbit (RSO) solution from GFZ (GeoForschungsZentrum Potsdam). The data screening for cycle slips is a particularly challenging procedure for LEO, which moves very fast in the middle of the ionospheric layer. It was found that data screening using SNR (signal to noise ratio) generates best results based on the residual analysis using RSO. It is expected that much better accuracy are achievable with refined prescreening procedure and optimized geometry of the satellites and ground stations.