This study simulated and analyzed a passive thermal control system for the design of a TUUSAT-1A microsatellite. The passive attitude magnet microsatellite is a 28 cm cube. This study analyzed satellite temperature distribution via both the node grid analysis model and the numerical iteration method to solve the nonlinear energy equation and achieve normal satellite components operation within a safe temperature. We also calculated temperatures with further, considerations at various orbital altitudes of 500Km, 300Km and 700Km, with sun-angles between plus and minus 45 degrees and at different spin speeds. The results were compared with various components of operating temperature and within their allowable ranges with an uncertainty margin of 5℃. The results show that without any thermal control system. The temperature of the simulation is about 51℃ ～ 62℃. And external coating protects the microsatellite operating temperature is maintained between 5 ～ 40℃ at different altitudes, sun angles and spin speeds. The simulated parameters of thermal control design proposed here could be helpful in future tasks.
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