• Publications of The Korean Astronomical Society
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• v.27 no.3
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• pp.39-47
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• 2012

MIRIS, Multi-purpose Infra-Red Imaging System, is the main payload of STSAT-3 (Korea Science & Technology Satellite 3), which will be launched in the end of 2012 (the exact date to be determined) by a Russian Dnepr rocket. MIRIS consists of two camera systems, SOC (Space Observation Camera) and EOC (Earth Observation Camera). During a shock test for the flight model stability in the launching environment, some lenses of SOC EQM (Engineering Qualification Model) were broken. In order to resolve the lens failure, analyses for cause were performed with visual inspections for lenses and opto-mechanical parts. After modifications of SOC opto-mechanical parts, the shock test was performed again and passed. In this paper, we introduce the solution for lens safety and report the test results.

• Journal of Astronomy and Space Sciences
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• v.19 no.4
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• pp.283-292
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• 2002

Electronic boards of Far-ultraviolet IMaging Spectrograph (FIMS) should be designed to maintain their performances, and their temperatures should be remained within the allowed temperatures in operational environments. Thermal analysis at the electronic board level has been performed, and it is confirmed the electronics parts could be kept within their allowed temperature ranges.

• Journal of Astronomy and Space Sciences
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• v.23 no.4
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• pp.425-434
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• 2006

The KASINICS (KASI Nea.-Infrared Camera System) is a ground-based instrument developed by the Korea Astronomy and Space Science Institute (KASI). We developed a temperature and vacuum monitoring system for operating the KASINICS. The system consists of hardware and software parts. The acquired data we saved on a hard disk in a real-time mode. This system on also be applied to general cryogenic instruments. We tested our monitoring system for the cooling and vacuum performance of the KASINICS. The results show that our system is efficient and stable for the operation of the KASINICS.

• Journal of Astronomy and Space Sciences
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• v.35 no.3
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• pp.195-200
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• 2018

The present paper describes the design of a Solid State Telescope (SST) on board the Korea Astronomy and Space Science Institute satellite-1 (KASISat-1) consisting of four [TBD] nanosatellites. The SST will measure these radiation belt electrons from a low-Earth polar orbit satellite to study mechanisms related to the spatial resolution of electron precipitation, such as electron microbursts, and those related to the measurement of energy dispersion with a high temporal resolution in the sub-auroral regions. We performed a simulation to determine the sensor design of the SST using GEometry ANd Tracking 4 (GEANT4) simulations and the Bethe formula. The simulation was performed in the range of 100 ~ 400 keV considering that the electron, which is to be detected in the space environment. The SST is based on a silicon barrier detector and consists of two telescopes mounted on a satellite to observe the electrons moving along the geomagnetic field (pitch angle $0^{\circ}$) and the quasi-trapped electrons (pitch angle $90^{\circ}$) during observations. We determined the telescope design of the SST in view of previous measurements and the geometrical factor in the cylindrical geometry of Sullivan (1971). With a high spectral resolution of 16 channels over the 100 keV ~ 400 keV energy range, together with the pitch angle information, the designed SST will answer questions regarding the occurrence of microbursts and the interaction with energetic particles. The KASISat-1 is expected to be launched in the latter half of 2020.

• Bulletin of the Korean Space Science Society
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• 2005.04a
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• pp.29-29
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• 2005

• Bulletin of the Korean Space Science Society
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• 2005.10a
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• pp.50-50
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• 2005

• The Bulletin of The Korean Astronomical Society
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• v.28 no.1
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• pp.43-43
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• 2003

• Bulletin of the Korean Space Science Society
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• 2009.04a
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• pp.64.1-64.1
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• 2009

• Bulletin of the Korean Space Science Society
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• 2009.04a
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• pp.44.1-44.1
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• 2009

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.22.1-22.1
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• 2011

Two dominant components of polar motion are the Chandler and the annual components. Recently, the existence of 500-day period component in the Earth's polar motion has been manifested. But its existence is not clear on Fourier spectrum. One cause of difficulty involved here is that the amplitudes of the two main components are slightly variable in time by certain amounts (Chandler: 0.15~0.28 arcsec, annual: 0.09~0.15 arcsec). A residual polar motion time series excluding the two main components for a time span between 1962 Jan and 2010 Nov from IERS C04 time series dataset was constructed by least square fitting. For faithful fitting, 43 time segments of 6.8 year length (each starts on January 1st of successive years) were separately acquired and later combined together. The period of dominant peak in the spectrum of this residual polar motion time series is 490 days. Next peaks have their periods as semi-annual, 300~330 days, ~560 days, 670 days, and 1360 days.