• 한국위성정보통신학회논문지
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• 제12권1호
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• pp.81-87
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• 2017

본 논문에서는 서로 다른 항목의 정보를 담고 있는 다종다형자료의 메타 정보를 하나의 시스템에서 통합하여 검색 및 관리할 수 있으며, 관리되고 있는 메타 데이터에서 사용자가 필요한 검색 항목을 자유롭게 정의할 수 있는 사용자 인터페이스를 제공할 수 있는 시스템에 대해 연구하였다. 본 시스템의 특징은 다종다형 메타정보 관리가 가능하며 다양한 시스템 간 손쉬운 통합을 지원할 수 있는 데이터베이스 통합 버스, 다종다형 자료들의 사용자별 맞춤 서비스가 가능한 사용자별 검색 항목 지정 설정이 있다. 본 논문에서 연구한 시스템은 현재 ICT 분야에서 각광받고 있는 빅데이터 관리가 가능할 것으로 판단되며 향후 다양한 분야의 다종다형자료들을 효과적으로 관리하고 다양한 환경을 가지고 있는 시스템 간 통합을 손쉽게 수행할 수 있을 것으로 판단된다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2005년도 심포지엄 논문집 정보 및 제어부문
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• pp.155-157
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• 2005

The Electrical Test Bed(ETB) integrates the test environment, required for acceptance tests of system level, prior to FM testing. The ETB will be used for the validation of system-level functions and interface between each subsystem. The FTB supports early functional and limited performance checkout of electrical subsystems. Therefore, it provides the environment for the verification of the Flight Software including AOCS, EPS, and TC&R simulators. These ETB will be composed of engineering version of spacecraft BUS, which are laid on the laboratory table.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2015년도 제46회 하계학술대회
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• pp.946-947
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• 2015

정지궤도 복합위성용 전력조절장치는 위성의 전력버스에 필요한 전력을 조절하고 배터리의 충전과 방전을 제어하고 관리한다. 전력조절장치의 용량은 1kw로 하고 태양 전지의 어레이는 4개의 패널로 구성되며 S3R(Sequential Switching Shunt Regulator)을 이용하여 조절된 버스전압은 완전조절 50Vdc으로 한다. 변환된 전력은 위성부하에 필요한 전력을 분배하는 PDM(Power Distribution Module)에 공급된다. 남은 전력은 BCR(Battery Charge Regulator)를 통해 배터리에 전력을 충전하고 전력이 부족할 때 BDR(Battery Discharge Regulator)를 통해 방전을 하여 버스전압에 전력을 공급한다.

• 전력전자학회:학술대회논문집
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• 전력전자학회 2019년도 추계학술대회
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• pp.176-177
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• 2019

인공위성의 전력요구가 증가함에도 전력손실과 무게증가를 최소화하기 위하여 버스전압은 점차 증가되고 있는 추세이다. 기존보다 높은 버스전압을 수용할 수 있는 새로운 전력변환장치가 개발되었으며 이에 적합한 태양전지배열기의 최적화 설계가 필요하다. 본 연구에서는 높은 버스전압의 전력변환장치에 적합한 태양전지배열기의 개발에 관하여 기술한다. 태양전지배열기는 태양전지의 직병렬 연결을 재구성하고 해석을 통하여 적합한 블록킹 다이오드 및 블리드 저항을 선정하여 최적화 설계가 이루어졌다. 설계된 태양전지배열기는 인공위성의 우주환경과 임무수명에 따른 감쇄요인을 반영하여 전력을 예측함으로써 요구조건의 만족여부를 확인하였다.

• 한국정보처리학회:학술대회논문집
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• 한국정보처리학회 2018년도 추계학술발표대회
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• pp.102-103
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• 2018

위성으로 송신하는 원격명령은 실시간 명령과 저장 명령, 메모리업로드 명령 등으로 구분된다. 저장 명령은 특정한 시간에 수행하는 절대시간 명령과 정해진 시간 간격에 따라 수행하는 상대시간 명령으로 구분할 수 있고, 절대시간 명령은 위성 본체에서 수행하는 명령과 탑재체에서 수행하는 명령으로 구분되고, 각각의 메모리 영역에 구분 저장된다. 지상으로부터 전송된 명령이 정상적으로 저장되었는지를 확인하기 위하여 메모리 덤프 명령을 통하여 해당 영역의 데이터를 전송받는다. 그런데 메모리 덤프로 받은 원시 데이터는 용량이 크고 연속적인 데이터 패턴으로 되어 있어 사용자가 바로 분석할 수 없으므로 별도의 파싱 프로그램이 요구된다. 본 논문은 위성으로부터 전송받은 임무명령 저장영역의 원시 데이터 내용을 사용자가 쉽게 분석할 수 있도록 하기 위해 개발된 파싱 프로그램에 대하여 서술한 것이다.

• 천문학회보
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• 제42권1호
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• pp.40.3-41
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• 2017

Korea Astronomy and Space Science Institute The observation of particles and waves using a single satellite inherently suffers from space-time ambiguity. Recently, such ambiguity has often been resolved by multi-satellite observations; however, the inter-satellite distances were generally larger than 100 km. Hence, the ambiguity could be resolved only for large-scale (> 100 km) structures while numerous microscale phenomena have been observed at low altitude satellite orbits. In order to resolve those spatial and temporal variations of the microscale plasma structures on the topside ionosphere, SNIPE mission consisted of four (TBD) nanosatellites (~10 kg) will be launched into a polar orbit at an altitude of 700 km (TBD). Two pairs of satellites will be deployed on orbit and the distances between each satellite will be from 10 to 100 km controlled by a formation flying algorithm. The SNIPE mission is equipped with scientific payloads which can measure the following geophysical parameters: density/temperature of cold ionospheric electrons, energetic (~100 keV) electron flux, and magnetic field vectors. All the payloads will have high temporal resolution (~ 16 Hz (TBD)). This mission is planned to launch in 2020. The SNIPE mission aims to elucidate microscale (100 m-10 km) structures in the topside ionosphere (below altitude of 1,000 km), especially the fine-scale morphology of high-energy electron precipitation, cold plasma density/temperature, field-aligned currents, and electromagnetic waves. Hence, the mission will observe microscale structures of the following phenomena in geospace: high-latitude irregularities, such as polar-cap patches; field-aligned currents in the auroral oval; electro-magnetic ion cyclotron (EMIC) waves; hundreds keV electrons' precipitations, such as electron microbursts; subauroral plasma density troughs; and low-latitude plasma irregularities, such as ionospheric blobs and bubbles. We have developed a 6U nanosatellite bus system as the basic platform for the SNIPE mission. Three basic plasma instruments shall be installed on all of each spacecraft, Particle Detector (PD), Langmuir Probe (LP), and Scientific MAGnetometer (SMAG). In addition we now discuss with NASA and JAXA to collaborate with the other payload opportunities into SNIPE mission.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2011년도 한국우주과학회보 제20권1호
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• pp.23.4-23.4
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• 2011

MIRIS is the main payload of the Science and Technology Satellite-3 (STSAT-3). which is being developed by KASI for infrared survey observation of the Galactic plane at Paschen alpha wavelength. Wideband filters in I and H band will also be used to observe cosmic infrared background. The MIRIS will perform astronomical observations in the near-infrared wavelengths of 0.9~2 ${\mu}m$ using a 256 ${\times}$ 256 Teledyne PICNIC FPA sensor providing a 3.67 ${\times}$ 3.67 degree field of view with a pixel scale of 51.6 arcsec. The flight model of the MIRIS has been recently developed, The system performance tests have been made in the laboratory, including opto-mechanics test, vibration test, thermal vacuum test and passive cooling test down to 200K, using a thermally controlled vacuum chamber. Several focus tests showed good agreements compared to initial design parameters. Recent efforts are being concentrated to improve the system performances, particularly to reduce readout noise level in electronics. After assembly and integration into the satellite bus, the MIRIS will be launched in 2012.

• 천문학논총
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• 제20권1호
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• pp.135-141
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• 2005

The FIMS(Far-ultraviolet IMaging Spectrograph), the main payload onboard the first Korean Science Technology SATellite, STSAT-1, has performed various astronomical observations, including the Cygnus Loop, Vela supernova remnants, LMC(Large Magellanic Cloud), since its launch on September 2003. It has been found that the attitude information provided by spacecraft bus system has the errors of more than about 10-15 arcmins due to the time offset problem and errors in attitude knowledge. We develop an algorithm for correction of position errors in FIMS data. The aspect for the FIMS data is determined by comparing the positions of observed bright stars with the Tycho-II and TD-1 catalogs. The position errors of the bright stars along the scanning (${\gamma}$) and spatial (${\delta}$) directions were considered as functions of ${\delta}$, ignoring errors in position angle. The corrected positions of the bright stars coincided very well to their Tycho-II and TD-I positions. The correction algorithm is essential for the FIMS data analysis, and is being used for the FIMS data analysis.

• Journal of Power Electronics
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• 제11권6호
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• pp.870-879
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• 2011

Regulated peak power tracking (RPPT) systems such as the series structure and the series-parallel structures are commonly used in satellite space power systems. However, these structures process the solar array power or the battery power to the load through two cascaded regulators during one orbit cycle, which reduces the energy transfer efficiency. Also the battery charging time is increased due to placement of converter between the battery and the solar array. In this paper a parallel structure has been proposed which can improve the energy transfer efficiency and the battery charging time for satellite space power RPPT systems. An analogue controller is used to control all of the required functions, such as load voltage regulation and solar array stabilization with maximum power point tracking (MPPT). In order to compare the system efficiency and the battery charging efficiency of the proposed structure with those of a series (conventional) structure and a simplified series-parallel structure, simulations are performed and the results are analyzed using a loss analysis model. The proposed structure charges the battery more quickly when compared to the other two structures. Also the efficiency of the proposed structure has been improved under different modes of solar array operation when compared with the other two structures. To verify the system, experiments are carried out under different modes of solar array operation, including PPT charge, battery discharge, and eclipse and trickle charge.

• 대한원격탐사학회지
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• 제28권6호
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• pp.693-704
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• 2012

Space-born remote sensing camera systems tend to be developed to have very high performances. They are developed to provide extremely small ground sample distance, wide swath width, and good MTF (Modulation Transfer Function) at the expense of big volume, massive weight, and big power consumption. Therefore, the camera system occupies relatively big portion of the satellite bus from the point of mass and volume. However, the camera systems for lunar exploration don't need to have such high performances. Instead, it should be versatile for various usages under various operating environments. It should be light and small and should consume small power. In order to be used for national program of lunar exploration, electro-optical versatile camera system, called MAEPLE (Multi-Application Electro-Optical Payload for Lunar Exploration), has been designed after the derivation of camera system requirements. A ground model of the camera system has been manufactured to identify and secure relevant key technologies. The ground model was mounted on an aircraft and checked if the basic design concept would be valid and versatile functions implemented on the camera system would worked properly. In this paper, results of design and functional test performed with the field campaigns and air-born imaging are introduced.