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Thermal Analysis of TRIO-CINEMA Mission
유제건,진호,선종호,정윤황,David Glaser,이동훈,Robert P. Lin 한국우주과학회 2012 Journal of Astronomy and Space Sciences Vol.29 No.1
Thermal analysis and control design are prerequisite essential to design the satellite. In the space environment, it makes satellite survive from extreme hot and cold conditions. In recent years CubeSat mission is developed for many kinds of purpose. Triplet Ionospheric Observatory (TRIO)–CubeSat for Ion, Neutral, Electron, MAgnetic fields (CINEMA) is required to weigh less than 3 kg and operate on minimal 3 W power. In this paper we describe the thermal analysis and control design for TRIO-CINEMA mission. For this thermal analysis, we made a thermal model of the CubeSat with finite element method and NX6.0 TMG software is used to simulate this analysis model. Based on this result, passive thermal control method has been applied to thermal design of CINEMA. In order to get the better conduction between solar panel and chassis, we choose aluminum 6061-T6 for the material property of standoff. We can increase the average temperature of top and bottom solar panels from -70°C to -40°C and decrease the average temperature of the magnetometer from +93°C to -4°C using black paint on the surface of the chassis, inside of top & bottom solar panels, and magnetometer.
유제건(Jaegun Yoo),박성우(Sung-Woo Park),정창훈(Chang-Hoon Jung),강성욱(Sung-Wook Kang),강동석(Dong-Seok Kang),정성훈(Sung-Hoon Jung) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
In the space environment, analysis of orbit beta angle and incident radiative heat flux of the Sun are essential prerequisites to thermal analysis and design a satellite. It makes a satellite to survive from extremely hot and cold conditions. Analysis of incident radiative heat flux is very important to allocate electronic boxes to panels of satellite. In this paper, orbit beta angle is derived from general LEO satellite considering 505 km, 97.4° inclination, sun-synchronous orbit and compared with orbit beta angle of LEO-B satellite. The TMM of satellite was made by using SINDA/FLUINT v5.6 software and used for orbit thermal analysis of the worst hot and cold cases. For the future, this study will be helpful to development of LEO satellite mission.