抄録
This paper presents a thermal design method of nano and micro satellites by one-nodal and two-nodal thermal analyses. The orbit is the sun-synchronous and circular orbit at an altitude of 500 km and at the local time at descending node of 11 o'clock. The attitude is pointing to the Earth. The combinations of optical properties, solar absorptivity and infrared emissivity, on surfaces of Inner Structure and Outer Structure under which the temperature of a satellite is within an allowable temperature range are clarified. The results show a correspondence relation between analytical methods and forms of heat transfer (heat conduction or radiation) between Inner Structure and Outer Structure. A thermal design in which there is little difference between analytical value and experimental value is realized by setting appropriate thermal control products on the contact faces between Inner Structure and Outer Structure. The combinations of optical properties are larger in the design focusing on radiation than in that focusing on heat conduction. A configuration of Inner Structure influences the combination. Finally, thermal design method by the one-nodal and two-nodal analyses which allows one to develop a satellite in short period at low cost is proposed.
