<![CDATA[Thermal control subsystem (TCS) as one of the satellite subsystems has a function for maintain a thermal control for over all the components of the satellite within their required temperature limits for alls mission phase. This objective can be reached with keeping the balance of energy, among incoming energy and discharge energy. In this paper temperature distribution (worst hot case and worst cold case) of nanosatellite in low earth orbit using some data assumptions for calculating the spherical, solar array and sphere of the satellite are used. For the sphere of the satellite is not describes in this paper. Temperature distribution of a cubsat was computed using SCDE (Spacecraft Control Design Engineering) based on the Microsoft Excel. It was created self by author using some references. The thermal analysis results show that average the maximum and minimum temperature’s based on low earth satellite’s altitude (400 km to 700 km) are 32.62°C and -75.32°C for the spherical of the satellite, and 67.15°C and -75.12°C for the solar array of the satellite.]]>
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