• 한국정보통신학회논문지
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• 제17권2호
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• pp.309-316
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• 2013

달 탐사 통신 시스템에 영향을 미치는 요소 중 하나인 태양활동은 오는 2013년 가을에 11년 주기로 나타나는 태양 활동 극대기를 맞이하며, 이에 따라 태양 폭발 빈도와 강도가 증가할 것으로 예상되고 있다. 태양 폭발은 지구 자기권에 영향을 미쳐 과학, 방송, 통신, 군사 위성 또는 탐사선 등의 오작동, 통신 두절, 장비 고장 등을 발생시키는 원인이 될 수 있으며, 이러한 문제점은 막대한 물리적, 경제적 손실을 가져올 수 있다. 따라서 태양 폭발이 달 탐사선에 미치는 영향에 대한 분석을 수행하여 예상되는 손실을 최소화해야 할 것이다. 본 논문에서는 탐사선의 생존성을 높이고 안정적인 통신 채널 운용을 위하여 태양 폭발에 따른 지상국 - 달 탐사선 간의 통신 모델과 그 성능을 분석한다.

• Journal of Astronomy and Space Sciences
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• 제28권3호
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• pp.203-216
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• 2011

To prepare for a future Korean lunar orbiter mission, semi-optimal lunar capture orbits using finite thrust are designed and analyzed. Finite burn delta-V losses during lunar capture sequence are also analyzed by comparing those with values derived with impulsive thrusts in previous research. To design a hypothetical lunar capture sequence, two different intermediate capture orbits having orbital periods of about 12 hours and 3.5 hours are assumed, and final mission operation orbit around the Moon is assumed to be 100 km altitude with 90 degree of inclination. For the performance of the on-board thruster, three different performances (150 N with $I_{sp}$ of 200 seconds, 300 N with $I_{sp}$ of 250 seconds, 450 N with $I_{sp}$ of 300 seconds) are assumed, to provide a broad range of estimates of delta-V losses. As expected, it is found that the finite burn-arc sweeps almost symmetric orbital portions with respect to the perilune vector to minimize the delta-Vs required to achieve the final orbit. In addition, a difference of up to about 2% delta-V can occur during the lunar capture sequences with the use of assumed engine configurations, compared to scenarios with impulsive thrust. However, these delta-V losses will differ for every assumed lunar explorer's on-board thrust capability. Therefore, at the early stage of mission planning, careful consideration must be made while estimating mission budgets, particularly if the preliminary mission studies were assumed using impulsive thrust. The results provided in this paper are expected to lead to further progress in the design field of Korea's lunar orbiter mission, particularly the lunar capture sequences using finite thrust.

• Journal of Astronomy and Space Sciences
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• 제28권1호
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• pp.55-62
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• 2011

The precise orbit determination (POD) of low earth orbiter (LEO) has complied with its required positioning accuracy by the double-differencing of observations between International GNSS Service (IGS) and LEO to eliminate the common clock error of the global positioning system (GPS) satellites and receiver. Using this method, we also have achieved the 1 m positioning accuracy of Korea Multi-Purpose Satellite (KOMPSAT)-2. However double-differencing POD has huge load of processing the global network of lots of ground stations because LEO turns around the Earth with rapid velocity. And both the centimeter accuracy and the near real time (NRT) processing have been needed in the LEO POD applications--atmospheric sounding or urgent image processing--as well as the surveying. An alternative to differential GPS for high accuracy NRT POD is precise point positioning (PPP) to use measurements from one satellite receiver only, to replace the broadcast navigation message with precise post processed values from IGS, and to have phase measurements of dual frequency GPS receiver. PPP can obtain positioning accuracy comparable to that of differential positioning. KOMPSAT-5 has a precise dual frequency GPS flight receiver (integrated GPS and occultation receiver, IGOR) to satisfy the accuracy requirements of 20 cm positioning accuracy for highly precise synthetic aperture radar image processing and to collect GPS radio occultation measurements for atmospheric sounding. In this paper we obtained about 3-5 cm positioning accuracies using the real GPS data of the Gravity Recover and Climate Experiment (GRACE) satellites loaded the Blackjack receiver, a predecessor of IGOR. And it is important to reduce the latency of orbit determination processing in the NRT POD. This latency is determined as the volume of GPS measurements. Thus changing the sampling intervals, we show their latency to able to reduce without the precision degradation as the assessment of their precision.

• Journal of Astronomy and Space Sciences
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• 제34권2호
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• pp.139-151
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• 2017

This paper presents an overview of deep space orbit determination software (DSODS), as well as validation and verification results on its event prediction capabilities. DSODS was developed in the MATLAB object-oriented programming environment to support the Korea Pathfinder Lunar Orbiter (KPLO) mission. DSODS has three major capabilities: celestial event prediction for spacecraft, orbit determination with deep space network (DSN) tracking data, and DSN tracking data simulation. To achieve its functionality requirements, DSODS consists of four modules: orbit propagation (OP), event prediction (EP), data simulation (DS), and orbit determination (OD) modules. This paper explains the highest-level data flows between modules in event prediction, orbit determination, and tracking data simulation processes. Furthermore, to address the event prediction capability of DSODS, this paper introduces OP and EP modules. The role of the OP module is to handle time and coordinate system conversions, to propagate spacecraft trajectories, and to handle the ephemerides of spacecraft and celestial bodies. Currently, the OP module utilizes the General Mission Analysis Tool (GMAT) as a third-party software component for high-fidelity deep space propagation, as well as time and coordinate system conversions. The role of the EP module is to predict celestial events, including eclipses, and ground station visibilities, and this paper presents the functionality requirements of the EP module. The validation and verification results show that, for most cases, event prediction errors were less than 10 millisec when compared with flight proven mission analysis tools such as GMAT and Systems Tool Kit (STK). Thus, we conclude that DSODS is capable of predicting events for the KPLO in real mission applications.

• 한국항공우주학회지
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• 제41권5호
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• pp.366-372
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• 2013

한국형 달탐사선은 국가 우주개발계획에 따라 한국형 발사체인 KSLV-2(Korea Space Launch Vehicle 2)에 탑재하여 2020년 이후 발사될 예정이다. 한국형 달탐사선은 무인 탐사선으로 궤도선과 착륙선 2종으로 구성되며 발사체의 탑재능력에 따라 발사중량 550kg 이내의 소형 경량으로 개발되어야 한다. 달탐사선 구조체는 임무 탑재장비의 수용 뿐 아니라 발사 및 운용환경에서 견딜 수 있도록 충분한 강성과 강도가 요구된다. 본 논문에서는 한국형 달탐사선 구조모델의 설계에 대한 선행 연구결과를 기술한다.

• Journal of Astronomy and Space Sciences
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• 제34권4호
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• pp.331-342
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• 2017

To ensure the successful launch of the Korea pathfinder lunar orbiter (KPLO) mission, the Korea Aerospace Research Institute (KARI) is now performing extensive trajectory design and analysis studies. From the trajectory design perspective, it is crucial to prepare contingency trajectory options for the failure of the first lunar brake or the failure of the first lunar orbit insertion (LOI) maneuver. As part of the early phase trajectory design and analysis activities, the required time of flight (TOF) and associated delta-V magnitudes for each recovery maneuver (RM) to recover the KPLO mission trajectory are analyzed. There are two typical trajectory recovery options, direct recovery and low energy recovery. The current work is focused on the direct recovery option. Results indicate that a quicker execution of the first RM after the failure of the first LOI plays a significant role in saving the magnitudes of the RMs. Under the conditions of the extremely tight delta-V budget that is currently allocated for the KPLO mission, it is found that the recovery of the KPLO without altering the originally planned mission orbit (a 100 km circular orbit) cannot be achieved via direct recovery options. However, feasible recovery options are suggested within the boundaries of the currently planned delta-V budget. By changing the shape and orientation of the recovered final mission orbit, it is expected that the KPLO mission may partially pursue its scientific mission after successful recovery, though it will be limited.

• 한국측량학회지
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• 제28권4호
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• pp.463-469
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• 2010

화성의 고도정보를 제공하는 MOLA 센서는 화성전역에 대한 데이터를 제공하지 못하므로, 수치표고모형을 만들기 위해서는 MOC-NA영상을 이용한 영상정합이 수행되어야만 한다. 그러나 특색(feature)이 적고 명암대비가 낮은 화성영상의 특성상, 자동 영상정합은 어려운 실정이다. 본 논문은 MOC-NA 영상에 대하여 영역기준 영상정합에 기반한 반 자동 영상정합의 알고리즘을 다룬다. 공액점을 나타내는 시드(seed)포인트 들이 수동으로 스테레오 영상에 추가되고 이를 바탕으로 특징점들이 자동으로 삽입된다. 각 영상의 특징점들은 서로의 초기 공액점으로 사용되며, 영역기준 영상정합으로 정제된다. 영상정합의 과정 중 정합에 실패한 점들은 초기 공액점의 위치를 정합에 성공한 주변의 여섯 점들을 이용하여 재 계산한 후 정제된다. 타깃영상과 검색영상의 역할을 바꾸어 수행한 영상정합의 질적 평가 결과, 97.3%의 점들이 한 화소 이하의 절대거리를 나타내었다.

• Journal of Astronomy and Space Sciences
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• 제33권4호
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• pp.323-333
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• 2016

In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the execution of the $1^{st}$ lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During the early design phase of the system, associate analysis is an essential design factor as the $1^{st}$ LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the $1^{st}$ LOI maneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the $1^{st}$ elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC) maneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based on the current results, including a contingency trajectory design plan.

• 대한원격탐사학회지
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• 제35권3호
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• pp.471-482
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• 2019

달 탐사용 고해상도 스테레오 카메라의 임무는 달 궤도선 및 착륙 선에 탑재되어 달 표면의 3차원 지형정보를 제공하는데 있다. 이를 통해, 달 착륙 후보지를 탐색하고 착륙 시에는 달 표면 근접에 따른 근거리 입체영상을 실시간으로 제공하여 정확한 지점에 착륙이 가능하도록 한다. 본 논문에서는 달 탐사선에 탑재되는 달 탐사용 고해상도 카메라 개발을 위한 지상모델인 다기능 스테레오 카메라를 활용하여 고해상도 스테레오 카메라에 요구되는 임무를 검증하고 결과를 분석하기 위해 지상검증 및 분석 시스템을 제안하였다. 지상검증 및 분석 시스템은 임무 검증을 위한 임무검증항목과 시험계획을 제공하며, 시험 수행 후 결과를 분석하게 된다. 이를 위해 본 논문에서는 달 지형과 유사한 지역을 대상으로 지상 임무항목시험 계획을 세우고, 항공촬영을 통해 스테레오 영상을 획득하였다. 분석장치를 통해 스테레오 영상으로부터 영상을 보정 및 매칭 후 수치표고모델(DEM)을 추출하고 3차원 영상을 생성하여 결과를 분석하였다. 달 탐사용 고해상도 카메라에 요구되는 임무수행항목이 검증되었고, 스테레오 영상을 처리할 수 있는 지상처리분석 시스템이 확보 되었다.

• 천문학회지
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• 제56권2호
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• pp.293-299
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• 2023

The Wide-Angle Polarimetric Camera (PolCam) is installed on the Korea's lunar orbiter, Danuri, which launched on August 5, 2022. The mission objectives of PolCam are to construct photometric maps at a wavelength of 336 nm and polarization maps at 461 and 748 nm, with a phase angle range of 0°-135° and a spatial resolution of less than 100 m. PolCam is an imager using the push-broom method and has two cameras, Cam 1 and Cam 2, with a viewing angle of 45° to the right and left of the spacecraft's direction of orbit. We conducted performance tests in a laboratory setting before installing PolCam's flight model on the spacecraft. We analyzed the CCD's dark current, flat-field frame, spot size, and light flux. The dark current was obtained during thermal / vacuum test with various temperatures and the flat-field frame data was also obtained with an integrating sphere and tungsten light bulb. We describe the calibration method and results in this study.