• 천문학논총
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• 제18권1호
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• pp.87-95
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• 2003

FIMS (Far-ultraviolet IMaging Spectrograph) is the main payload of STSAT-1 satellite which was successfully launched on September 27, 2003. The optical system of FIMS consists of two sets of parabolic cylinder mirror, slit, ellipsoidal reflection grating, and baffle system. We designed two types of baffle system for the FIMS: FOV baffle and order baffle. FOV baffle in the mirror house controls the field of view, and the order baffle in the vacuum box blocks the rays reflected rays by different orders.

• 한국항공우주학회지
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• 제38권8호
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• pp.798-805
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• 2010

전구조 소형 복합재 위성인 과학기술위성 3호가 국내 최초로 개발되었다. 과학기술위성 3호는 기존의 위성과 달리 알루미늄 프레임이 없는 구조로 되어있으며 알루미늄 코어에 적층복합재 스킨을 가진 샌드위치 패널의 조합으로 구성되었다. 이 복합재 패널의 결합으로 구성된 격자형태의 공간에 다수의 전장박스와 탑재체 및 장치들이 장착된다. 본 연구는 과학기술위성 3호의 랜덤진동 응답에 관한 연구이며 이를 위하여 FEA 해석과 시험이 수행 되었다. 진동시험 결과와 전산해석결과를 서로 상호 비교 검토함으로써 위성의 진동 특성을 규명하고 결과의 신뢰성을 검증하였다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2009년도 한국우주과학회보 제18권2호
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• pp.43.2-43.2
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• 2009

Electron microbursts are the intense electron precipitation which durations are less than one second. We measured the energy spectra of the microbursts from 170 keV to 340 keV with solid state detectors aboard the low-altitude (680km), polar-orbiting Korean STSAT-1 (Science and Technology SATellite). The data showed that the loss cone at these energies is empty except when microbursts abruptly appear and fill the loss cone in less than 50 msec. This fast loss cone filling requires pitch angle diffusion coefficients larger than ~ 10-2rad2/sec, while ~10-5 rad2/sec was proposed by a wave particle interaction theory. We recalculated the diffusion coefficient, and reviewed of electron microburst generation mechanism with test particle simulations. This simulation successfully explained how chorus waves make pitch angle diffusion within such short period. From considering the resonance condition between wave and electrons, we also showed ~ 100 keV electrons could be easily aligned to the magnetic field, while ~ 1MeV electrons filled loss cone partially. This consideration explained why precipitating microbursts have lower e-folding energy than that of quasi-trapped electrons, and supports the theory that relativistic electron microbursts that have been observed by satellite in-situ measurement have same origin with ~100 keV electron microbursts that have been usually observed by balloon experiments.

• 천문학논총
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• 제22권4호
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• pp.177-181
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• 2007

We present the sensitivity calculation results for observing the Cosmic Infrared Background (CIRB) by the Multi-purpose IR Imaging System (MIRIS), which will be launched in 2010 as a main payload of the Science and Technology Satellite 3 (STSAT-3). MIRIS will observe in I ($0.9{\sim}1.2um$) and H ($1.2{\sim}2.0um$) band with a $4{\times}4$ degree field of view to obtain the large scale structure (${\sim}3$ degree) of the CIRB. With the given specifications of the MIRIS, our sensitivity calculation results show that the MIRIS has a detection limit of ${\sim}9\;nW\;m^{-2}\;sr^{-1}$ (I band) and ${\sim}6\;nW\;m^{-2}\;sr^{-1}$ (H band), which is appropriate to observe the large scale structure of CIRB.

• 천문학회보
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• 제40권1호
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• pp.55.1-55.1
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• 2015

The first Korean infrared space telescope MIRIS (Milti-purpose InfraRed Imaging System) was successfully launched in November 2013, as the main payload of Korean STSAT-3 (Science and Technology Satellite-3). After initial on-orbit operation for verification, the observations have been made with MIRIS for the fluctuation of Cosmic Infrared Background and the Galactic Plane survey. For the study of near-infrared background, MIRIS completed the survey of large areas (> $10^{\circ}{\times}10^{\circ}$ around the pole regions: the north ecliptic pole (NEP), the north and south Galactic poles (NGP, SGP). We are also continuously and frequently monitoring the NEP region for the instrumental calibration and the zodiacal light study. One the other hand, the Paschen-${\alpha}$ Galactic plane survey has been carried out using two narrow-band filters (at $1.88{\mu}m$ and $1.84+1.92{\mu}m$) of MIRIS. This survey is planning to cover the whole Galactic plane with the latitude of ${\pm}3^{\circ}$, and the longitude regions of $+280^{\circ}<l<360^{\circ}$ and $0^{\circ}<l<+210^{\circ}$ have been completed (~ 80%) by February 2015. The data are still under the stage of reduction and analysis, and we present some preliminary results.

• 한국항공우주학회지
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• 제42권2호
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• pp.158-164
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• 2014

IADC의 '25년 규정'에 의해 미션종료 된 저궤도 인공위성은 25년 이내에 지구로 재진입, 소각 폐기되도록 권고하고 있다. 이때 인공위성의 부품일부 또는 다수가 살아남아 지상에 충돌할 경우 인명 및 재산피해를 낼 수 있다. 우리나라의 경우 저궤도 위성으로서 아리랑 인공위성과 과학기술위성을 운용 중에 있으며 임무종료 후에는 모두 대기권 재진입을 통한 폐기처리가 필수이다. 따라서 본 논문에서는 ESA의 DRAMA내부의 SARA(Re-entry Survival and Risk Analysis)모듈을 이용하여 지상피해가 예측되는 크기인 가상위성의 추락궤적 및 생존부품을 분석하고 그에 따른 지상충돌확률, 피해확률을 분석하였다. 분석결과 198.831kg이 생존할 것으로 예상되며 추락지점이 한반도일 경우 전체 피해면적은 $15.2742m^2$, 피해확률은 5.9614E-03(2D)일 것으로 예상된다.

• 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.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2011년도 한국우주과학회보 제20권1호
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• pp.20.1-20.1
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• 2011

We present the results of far-ultraviolet (FUV) observations of comet C/2001 Q4 (NEAT) obtained with Far-ultraviolet Imaging Spectrograph (FIMS) on board the Korean microsatellite STSAT-1, which operated at an altitude of 700 km in a sun-synchronous orbit. FIMS is a dual-channel imaging spectrograph (S channel 900-1150 ${\AA}$, L channel 1350-1750 ${\AA}$, ${\lambda}/{\Box}{\lambda}$ ~ 550) with large image fields of view (S: $4^{\circ}.0{\times}4'.6$, L: $7^{\circ}.5{\times}4'.3$, angular resolution 5'-10') optimized for the observation of diffuse emission of astrophysical radiation. Comet C/2001 Q4 (NEAT) was observed with a scanning survey mode when it was located around the perihelion between 8 and 15 May 2004. Several important emission lines were detected including S I (1425, 1474 ${\AA}$), C I (1561, 1657 ${\AA}$) and several emission lines of CO $A1{\cap}-X1{\sum}+$ system in the L channel. We estimated QCO = ($2.58\;{\pm}\;0.64)\;{\times}\;1028$ s-1 from the production rate of CO 1510 ${\AA}$. We obtained L-channel image which have map size of $5^{\circ}{\times}5^{\circ}$. The image was constructed for the wavelength band of L-channel (1350-1750 ${\AA}$).We also obtained radial profile of S I, C I, CO with line fitting from central coma.

• Journal of Astronomy and Space Sciences
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• 제21권4호
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• pp.383-390
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• 2004

2003년 9월에 발사되어 현재 임무수행중인 과학기술위성1호의 주탑재체 원자외선 분광기의 감도측정을 수행하였다. 이를 위하여 2003년 11월부터 2004년 5월의 기간동안 백색왜성 G191B2B와 O형 별인 Alpha-Cam, HD93521을 관측하였으며, 그 관측 데이터와 HUT(Hopkins Ultraviolet Telescope) 데이터를 비교하여 원자외선 분광기의 전 파장영역에 대한 유효면적을 계산하고, 그 결과를 비교 분석하였다.

• Journal of Astronomy and Space Sciences
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• 제28권3호
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• pp.225-232
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• 2011

We have designed and manufactured the Earth observation camera (EOC) of multi-purpose infrared imaging system (MIRIS). MIRIS is a main payload of the STSAT-3, which will be launched in late 2012. The main objective of the EOC is to test the operation of Korean IR technology in space, so we have designed the optical and mechanical system of the EOC to fit the IR detector system. We have assembled the flight model (FM) of EOC and performed environment tests successfully. The EOC is now ready to be integrated into the satellite system waiting for operation in space, as planned.