• Proceedings of the KSRS Conference
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• 1998.09a
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• pp.355-360
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• 1998

A small package of plasma instruments, Space Physics Sensor, will monitor the space environment and its effects on microelectronics in the low altitude region as it operates on board the KOMPSAT-1 from 1999 over the maximum of the solar cycle 23. The Space Physics Sensor (SPS) consists of two parts: the Ionospheric Measurement Sensor (IMS) and the High Energy Particle Detector (HEPD). IMS will make in situ Measurements of the thermal electron density and temperature, and is expected to provide a global map of the thermal electron characteristics and the variability according to the solar and geomagnetic activity in the high altitude ionosphere of the KOMPSAT-t orbit. HEPD will measure the fluxes of high energy protons and electrons, monitor the single event upsets caused by these energetic charged particles, and give the information of the total radiation dose received by the spacecraft. The continuous operation of these sensors, along with the ground measurements such as incoherent scatter radars, digital ionosondes and other spacecraft measurements, will enhance our understanding of this important region of practical use for the low earth orbit satellites.

• The Bulletin of The Korean Astronomical Society
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• v.31 no.1
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• pp.58.2-58.2
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• 2006

• The Bulletin of The Korean Astronomical Society
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• v.32 no.1
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• pp.42.1-42.1
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• 2007

• The Bulletin of The Korean Astronomical Society
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• v.24 no.2
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• pp.89-89
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• 1999

• The Bulletin of The Korean Astronomical Society
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• v.41 no.2
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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.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.132.1-132.1
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• 2012

Radiation Belt Environment (RBE) model has developed to understand radiation belt dynamics as it considers whistler mode hiss and chorus waves which is responsible for relativistic electron acceleration and precipitation. Recently, many studies on electron loss by pitch-angle scattering have reported that elctromagnetic ion cyclotron (EMIC) wave is also responsible for main loss mechanism in dusk and equatorial regeion. Here, we attempt to incorporate EMIC into RBE model simulation code to understand more detailed physical dynamics in Radiation belt environemnt. We compare this developed model to data during storm events where both of electron loss and EMIC waves were detected.

• The Bulletin of The Korean Astronomical Society
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• v.39 no.2
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• pp.108.1-108.1
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• 2014

Near-infrared Imaging Spectrometer for Star formation history (NISS), one of the main payloads of NEXTSat-1, is being developed by Korea Astronomy & Space Science Institute (KASI). Since NISS adopts an infrared reflecting optical system, its performance is highly sensitive to changes in system temperature. Therefore, it is important to figure out the temperature through thermal analysis and cooling tests in order to optimize the optical system design. We conducted thermal analysis of NISS for the recently updated model, and obtained steady state temperature of the optical system for two cases of satellite attitude: about 190 K for the Normal case and about 210 K for the Hot case. In this paper, we present thermal design of NISS and the preliminary thermal analysis results.

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.101-101
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• 2004

• Nuclear Engineering and Technology
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• v.55 no.1
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• pp.364-372
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• 2023

The space reactor is the primary energy supply for future space vehicles and space stations. The radiator is one of the essential parts of a space reactor. Therefore, the research on radiators can improve the heat dissipation power, reduce the quality of radiators, and make the space reactor smaller. Based on MOOSE multi-physics numerical calculation platform, a simulation program for the combination of heat pipe and fin at the end of heat pipe radiator is developed. It is verified that the calculation result of this program is accurate and the calculation speed is fast. Analyze the heat transfer characteristics of the combination with heat pipe and fin, and obtain its internal temperature field. Based on the calculation results, the influence of structural parameters on the heat dissipation power is analyzed. The results show that when the fin width is 0.25 m, fin thickness is 0.002 m, condensing section length is 0.5425 m and heat pipe radius is 0.014 m, the power-mass ratio is the highest. When the temperature is 700K-900K, the heat dissipation power increases 41.12% for every 100K increase in the operating temperature. Smaller fin width and thinner fin thickness can improve the power-mass ratio and reduce the radiator quality.

• Bulletin of the Korean Space Science Society
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• 1994.09a
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• pp.35-35
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• 1994

No Abstract. See Full-text