• 한국항공우주학회지
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• 제49권2호
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• pp.129-138
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• 2021

최근 다양한 지상 및 우주 임무 수행을 위한 위성 개발이 활발히 진행되고 있음에 따라 위성의 고정밀·고기동성을 고려한 위성 자세제어 또한 요구되는 추세이다. 임무 수행 최적화를 위하여 고기동성의 제어 모멘트 자이로(Control Moment Gyros, CMG)를 위성에 장착하여 반작용 휠(Reaction Wheel, RW)과 같은 기존의 구동기에서 비롯되는 기동 제약을 완화시킬 수 있다. 또한, 구동기 자체의 제약 특성으로 인하여 위성의 각속도 제한이 발생하게 된다. 본 논문에서는 이를 고려한 CSCMG(Constant Speed CMG)장착 위성의 자세제어를 위하여 슬라이딩 모드 기반 제어기를 설계하였고, 리아푸노프 안정성을 확인하였으며 마지막으로 수치 시뮬레이션을 통하여 제어기 성능 분석을 진행하였다.

• Journal of Astronomy and Space Sciences
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• 제35권4호
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• pp.253-261
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• 2018

Korea Astronomy and Space Science Institute (KASI) has been developing the space optical and laser tracking (SOLT) system for space geodesy, space situational awareness, and Korean space missions. The SOLT system comprises satellite laser ranging (SLR), adaptive optics (AO), and debris laser tracking (DLT) systems, which share numerous subsystems, such as an optical telescope and tracking mount. It is designed to be capable of laser ranging up to geosynchronous Earth orbit satellites with a laser retro-reflector array, space objects imaging brighter than magnitude 10, and laser tracking low Earth orbit space debris of uncooperative targets. For the realization of multiple functions in a novel configuration, the SOLT system employs a switching mirror that is installed inside the telescope pedestal and feeds the beam path to each system. The SLR and AO systems have already been established at the Geochang station, whereas the DLT system is currently under development and the AO system is being prepared for testing. In this study, the design and development of the SOLT system are addressed and the SLR data quality is evaluated compared to the International Laser Ranging Service (ILRS) tracking stations in terms of single-shot ranging precision. The analysis results indicate that the SLR system has a good ranging performance, to a few millimeters precision. Therefore, it is expected that the SLR system will not only play an important role as a member of the ILRS tracking network, but also contribute to future Korean space missions.

• 천문학논총
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• 제32권1호
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• pp.1-4
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• 2017

Some after-dinner thoughts on the giants of infrared space astronomy. I here describe important events in infrared astronomy starting from 1964 when I started working on my PhD. Here I describe how I became involved in IRAS, Infrared Space Observatrory (ISO), Herschel, Spitzer and AKARI, together with important events that led to these great missions.

• 한국항공우주학회지
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• 제37권3호
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• pp.267-274
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• 2009

최근 무인 항공기(Unmanned Aerial Vehicle, UAV)는 다양한 임무수행이 가능한 무인 시스템이라는 점에서 크게 주목받고 있다. 특히 정찰, 추적 등의 임무는 영상을 이용하여 임무 수행이 이루어진다. 소형 무인 항공기의 경우 중량과 비용을 고려하여 단안 영상을 이용하는 임무 수행 연구가 활발하게 이루어지고 있다. 그러나 실제 지표면과 목표물이 고도 차이를 가지고 있어, 영상의 상대깊이를 고려하지 않은 3차원 거리는 임무 수행 시 오차 요인으로 작용 할 수 있다. 본 연구에서는 상대 깊이 추정을 위한 평균이동 알고리즘, 광류, 부분 공간법에 관하여 차례로 제시한다. 평균이동 알고리즘은 영상 내 목표물 추적과 관심영역을 결정하며 광류는 영상의 자기를 이용한 영상 이동 정보를 포함한다. 마지막으로 부분 공간법은 영상안의 움직임을 추정하며 각 영역의 상대깊이를 결정한다.

• 천문학회보
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• 제41권2호
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• pp.37.2-37.2
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• 2016

MIRIS (Multi-purpose InfraRed Imaging System) is a compact near-infrared space telescope launched in 2013 November as the main payload of STSAT-3 (Science and Technology Satellite 3). The main missions of MIRIS are 1) the $Pa{\alpha}$ line survey along the Galactic plane, 2) the large area (${\sim}10^{\circ}{\times}10^{\circ}$) surveys of three pole regions (north ecliptic pole, and north and south Galactic poles), and 3) the monitoring observations toward the north ecliptic pole. MIRIS started observations for the main missions in 2014 March and finished in 2015 May. While MIRIS was taking the observation data and afterward, we are continuing the analysis of data. Based on the results from analysis, the data reduction pipeline has been revised. In this talk, we introduce the revised version of the MIRIS data reduction pipeline and the status of the data reduction and anlaysis.

• Journal of Astronomy and Space Sciences
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• 제34권3호
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• pp.225-235
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• 2017

The energy balance in a satellite needs to be designed properly for the satellite to safely operate and carry out successive missions on an orbit. In this study, an analysis program was developed using the MATLAB(R) graphic user interface (GUI) for nanosatellites. This program was used in a simulation to confirm the generated power, consumed power, and battery power in the satellites on the orbit, and its performance was verified with applying different satellite operational modes and units. For data transmission, STK(R)-MATLAB(R) connectivity was used to send the generated power from STK(R) to MATLAB(R) automatically. Moreover, this program is general-purpose; therefore, it can be applied to nanosatellites that have missions or shapes that are different from those of the satellites in this study. This power simulation tool could be used not only to calculate the suitable power budget when developing the power systems, but also to analyze the remaining energy balance in the satellites.

• Journal of Astronomy and Space Sciences
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• 제28권1호
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• pp.63-70
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• 2011

The needs for satellite formation flying are gradually increasing to perform the advanced space missions in remote sensing and observation of the space or Earth. Formation flying in low Earth orbit can perform the scientific missions that cannot be realized with a single spacecraft. One of the various techniques of satellite formation flying is the determination of the precise baselines between the satellites within the formation, which has to be in company with the precision validation. In this paper, the baseline of Gravity Recovery and Climate Experiment (GRACE) A and B was determined with the real global positioning system (GPS) measurements of GRACE satellites. And baseline precision was validated with the batch and sequential processing methods using K/Ka-band ranging system (KBR) biased range measurements. Because the proposed sequential method validate the baseline precision, removing the KBR bias with the epoch difference instead of its estimation, the validating data (KBR biased range) are independent of the data validated (GPS-baseline) and this method can be applied to the real-time precision validation. The result of sequential precision validation was 1.5~3.0 mm which is similar to the batch precision validation.

• 천문학회보
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• 제46권1호
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• pp.42.2-43
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• 2021

We address a question of what are three main channels that can best translate other channels in ultraviolet (UV) and extreme UV (EUV) observations. For this, we compare the image translations among the nine channels of the Atmospheric Imaging Assembly on the Solar Dynamics Observatory using a deep learning model based on conditional generative adversarial networks. In this study, we develop 170 deep learning models: 72 models for single-channel input, 56 models for double-channel input, and 42 models for triple-channel input. All models have a single-channel output. Then we evaluate the model results by pixel-to-pixel correlation coefficients (CCs) within the solar disk. Major results from this study are as follows. First, the model with 131 Å shows the best performance (average CC = 0.84) among single-channel models. Second, the model with 131 and 1600 Å shows the best translation (average CC = 0.95) among double-channel models. Third, among the triple-channel models with the highest average CC (0.97), the model with 131, 1600, and 304 Å is suggested in that the minimum CC (0.96) is the highest. Interestingly they are representative coronal, photospheric, and chromospheric lines, respectively. Our results may be used as a secondary perspective in addition to primary scientific purposes in selecting a few channels of an UV/EUV imaging instrument for future solar satellite missions.

• 우주기술과 응용
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• 제3권2호
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• pp.101-117
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• 2023

우주상에 존재하는 우주물체에 접근하여 궤도상에서 제거하는 능동 제거 기술(active debris removal, ADR)과 연료 충전, 배터리 교환 등의 위성의 수명연장을 위한 기술인 궤도상 서비싱(on-orbit servicing)은 우주물체의 증가와 함께 그 관심이 커지고 있다. 인공위성연구소에서는 국내에서 발사되었던 국가 자산 중 임무가 종료된 후 궤도상에서 여전히 우주를 돌고 있는 국가 우주자산을 포획 및 제거하는 목적의 위성을 개발하기 위한 연구를 수행 중에 있다. ADR 소형위성은 지금껏 국내에서 개발되었던 지구 및 우주환경 관측 위성과 다르게 랑데부/도킹 기술 등을 포함한 우주 탐사 임무 등 미래 임무에 요구되는 기술을 구현 및 실증하는 것을 주요 임무로 가지고 있다. 본 논문에서는 여러 국가 우주자산들 중 1990년대에 발사된 우리별 위성의 포획 및 제거 임무를 갖고 있는 ADR 소형위성의 궤도 전이 방법에 대해서 소개한다. 소형 위성은 무게가 약 200 kg 이하가 되도록 개발을 수행할 예정이고, 2027년 한국형 발사체를 통해 궤도상에 투입되는 상황을 가정하여 임무를 설계했다. 특히, 지구의 J2 섭동력을 이용해서 목표물과 다른 RAAN 일변화를 만들어 줌으로써, 목표물로의 궤도면 변경을 직접 천이 방식과 비교하여 더 적은 연료를 이용하는 전략을 구성하였다. 이 방법을 이용하여 소형위성급 무게의 위성으로 우주쓰레기 제거 임무를 가능하게 하며, 뉴스페이스 시대에 새로운 형태의 우주탐사를 수행하는 기술 검증 플랫폼이 될 것으로 기대한다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2009년도 한국우주과학회보 제18권2호
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• pp.48.1-48.1
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• 2009

In recent years, many candidates for extra-solar planet have been discovered from various measurement techniques. Fueled by such discoveries, new space missions for direct detection of earth-like planets have been proposed and actively studied. TPF instrument is a fair example of such scientific endeavors. One of the many technical problems that space missions such as TPF would need to solve is deconvolution of the collapsed (i.e. spatially and temporally) spectral signal arriving at the detector surface and the deconvolution computation may fall into a local minimum solution, instead of the global minimum solution, in the optimization process, yielding mis-interpretation of the spectral signal from the potential earth-like planets. To this extend, observational and theoretical understanding on the spectral bio-signal from the Earth serves as the key reference datum for the accurate interpretation of the planetary bio-signatures from other star systems. In this study, we present ray tracing computational model for the on-going simulation study on the Earth bio-signatures. A multi-layered atmospheric model and sea ice variation model were added to the existing target Earth model and a hypothetical space instrument (called AmonRa) observed the spectral bio-signals of the model Earth from the L1 halo orbit. The resulting spectrums of the Earth show well known "red-edge" spectrums as well as key molecular absorption lines important to harbor life forms. The model details, computational process and the resulting bio-signatures are presented together with implications to the future study direction.