Abstract
A new procedure for the thermal design of micro- and nano-satellites is proposed for completing the thermal design of micro- and nano-satellites within about one year. First, two concepts of thermal design are considered for maintaining the temperature change of units within an allowable range. One concept involves decreasing the temperature change of units by using the whole thermal capacity of the micro- and nano-satellite. The other concept involves decreasing the temperature change of the inner structure on which units with a narrow allowable temperature range are mounted and which is insulated conductively from the outer structure. Then, the temperatures of micro- and nano-satellites designed with the former concept are calculated using a one-node analysis method. The temperatures of micro- and nano-satellites designed with the latter concept are calculated using a two-node analysis method. The combinations of optical properties of the structures and units to maintain the temperature of units within the allowable range are obtained by using one- or two-node analysis. Finally, the multinode analyses are carried out to obtain a detailed design based on the optical properties obtained from the one-node analysis or two-node analysis. This thermal design procedure is applied to the Hodoyoshi-1 satellite, which is about 50 cm wide, 50 cm deep, 50 cm high, has a mass of about 50 kg, two inner plates, and solar cells on the body, flies on the Sun-synchronous orbit at the altitude of 500 km, and is pointing to the Earth. The thermal design of this micro-satellite was completed within about ten months. Possible problems with the procedure are tested, and the procedure is verified.
