Abstract:
The thermal control of future nanosatellite will be challenging due to dedicated panel surface area for radiation. The thermal control concept is to keep the payload within allowable temperature ranges. In order to predict the temperature for a nanosatellite in orbit, a basic thermal model of the nanosatellite was designed and analyzed. A thermal control system of the nanosatellite at an altitude 600 km with an inclination of 98 is presented. A thermal analysis of the nanosatellite was also performed with different altitudes from 500 km to 2000 km. A thermal control analysis of CubeSat's passive thermal control system was conducted. A temperature distribution of the solutions was computed. All electronic equipment and structural parts were within allowable temperatures, except the batteries. The batteries were out of their allowed range of temperatures in the cold case condition. The results of the study showed that the panel surface temperature results for different altitudes and panel combination are highly sensitive by the chosen surface coating of the nanosatellite. (C) 2014 Elsevier Ltd. All rights reserved.
