• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.60-64
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• 2005

STSAT-2 will demonstrate the scientific mission(acquisition of brightness temperature of the earth at 23.8 GHz and 37 GHz) and spacecraft technologies(laser ranging, frame-type satellite structure, Dual-head star tracker, CCD sun sensor, pulsed plasma thruster, etc.). In this paper STSAT-2 satellite system is described. It includes the definition of the system and the overview of payloads and BUS.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.189.2-189.2
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• 2012

과학기술위성 3호는 드네프르 발사체에 의해서 클러스터 형태로 발사될 예정이다. 본 논문에서는 과학기술위성 3호의 발사와 관련된 기계적 인터페이스, 전기적 인터페이스, 궤도 인터페이스, 발사장 인터페이스, 환경 인터페이스 등을 세부 적으로 기술한다. 이러한 인터페이스를 바탕으로 소형위성의 클러스터 발사의 기본적은 개념을 정의 할 수 있으며, 추후 소형위성 발사와 관련된 기본 기술을 확인 할 수 있다.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.61-61
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• 2004

과학기술위성 1호(STSAT-1)는 위성의 자세를 제어하기 위하여 Reaction Wheel Assembly(RWA)를 적용하였으며, 위성의 무게중심에 Wheel의 회전수에 비례하는 관성모멘트를 발생시켜 자세를 제어하였다. 과학기술위성 2호(STSAT-2)는 과학기술위성 1호에 적용하였던 반작용휠(RWA)과 펄스형태로 동작시켜 위성의 자세 및 궤도제어를 위하여 요구하는 추력을 얻을 수 있는 펄스형 전기 추진시스템(Pulsed Plasma Thruster: PPT)이 탑재된다. (중략)

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.79-85
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• 2004

In this study, the operations concept of STSAT-2 which will be launched by KSLV-1, the first Korean Space Launch Vehicle, from Naro is explained. The major tasks of STSAT-2 is acquiring Lyman-alpha images of Sun by LIST(Lyman-alpha Imaging Solar Telescope) payload and the exact position of the satellite by calculating distance between STSAT-2 and SLR ground stations using SLR(Satellite Laser Ranging) payload. Also spacecraft technology verification is performed.

• Proceedings of the Optical Society of Korea Conference
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• 2003.02a
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• pp.98-99
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• 2003

2005년 국산 소형위성 발사체에 탑재되어 발사 될 예정으로, 과학기술위성2호의 개발이 2002년 10월부터 시작되었다. 과학기술위성2호는 약 100kg의 소형위성으로, 경사각 60～80$^{\circ}$의 300km x 1500km 타원궤도에 발사될 것으로 예상되고 있으며, 라만-a태양촬영망원경(LIST, Larman-a Imaging Solar Telescope)과 레이저정밀거리측정용 반사경이 각각 주 및 부 탑재체로 탑재될 예정이다. 위성레이저정밀거리측정(SLR, Satellite Laser Ranging)이란 위성간의 거리를 가장 정확하게 측정할수 있는 축지학적 기술이다. (중략)

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.142-147
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• 2004

Satellite laser ranging (SLR), which is the most accurate geodetic method for precise orbit determination of artificial satellites, will be used to determine the precise orbit of STSAT2. This paper will present the development of a Laser Reflector Array (LRA) of STSAT2. Currently one LRA was designed, analyzed, manufactured, optically tested and assembled.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.93-98
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• 2005

STSAT-2 will be launched on December 2007 by the first Korean launch vehicle KSLV-1, and its one of the main instruments is DREAM (Dual Channel Radio Frequency and Environment Atmosphere Monitoring) which detects a signal for atmosphere from the Earth by using micro-wave signal. The STSAT-2 has many units for technology demonstration such as FDSS (Fine Digital Sun Sensor) and DHST (Dual Head Star Tracker) including PPT (Pulsed Plasma Thruster) for attitude control and momentum dumping in the space. In this paper, the power budget analysis for STSAT-2 will be studied and provided for supporting the whole mission life time during the mission of its spacecraft.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.29-36
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• 2011

The Science and Technology Satellite-3 (STSAT-3) is based on the KITSAT-1, 2, 3 and STSAT-1, 2 which were Korea micro-satellites for the mission of space and earth science. The objectives of the STSAT-3 are to support earth and space sciences in parallel with the demonstration of spacecraft technology. The STSAT-3 carries an infrared (IR) camera for space & earth observation and an imaging spectrometer for earth observation. The IR payload instrument of the STSAT-3, Multi-purpose Infrared Imaging System (MIRIS), will observe the Galactic plane and North/South Ecliptic poles to research the origin of universe. The secondary payload instrument, Compact Imaging Spectrometer (COMIS), images the Earth's surface. The data acquired from COMIS are expected to be used for various application fields such as monitoring of disaster management, water quality studies, and farmland assessment. In this paper we present the operations concept of STSAT-3 which will be launched into a sun-synchronous orbit at a nominal altitude of 600km in late 2012.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.507-517
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• 2010

The KOREAN AIR - R&D Center has developed a solar array for STSAT-2 Flight Model, SaTReC-KAIST, using a fully localized technology and has verified the performance through a launch vibration test, orbit environment test and electrical performance test. The solar array will be launched at NARO Space Center by KSLV-I which is the first Korean launch vehicle, in May 2010. In this paper, a current-voltage curve that shows the power characteristics of solar arrays was derived by applying elements that affects the power performance of STSAT-2's solar arrays to the solar cell equivalent models. The result was compared to LAPSS test results, and accuracy of the solar cell equivalent model and the power performance simulation has been analyzed.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.55-63
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• 2007

STSAT-2 (Science & Technology SATellite-2) is a Korea micro-satellite which will be launched at NARO Space center in Koheung, Korea. Launch vehicle for STSAT-2 is KSLV-1 (Korea Space Launch Vehicle-1) which is the first development in Korea space launch vehicle program. Starting development in 2002 EM(Engineering Model), PFM(Proto-Flight Model), and FM(Flight Model) were developed completely. Electrical functional test, space environmental test, and launch vehicle environmental test on system level are performed for testing those development models. In this paper we report the results of STSAT-2 PFM space environmental test and launch vehicle environmental test which is successfully completed.