抄録
"HODOYOSHI-1" is the a micro satellite which is about 60 cm cube and about 60 kg. This satellite is scheduled to be launch at the end of 2012 into a sun-synchronous orbit of the altitude 500 to 600 km for optical remote sensing mission. Using Fortran and thermal analysis software "Thermal Desktop", thermal design has been performed for this satellite. One-nodal analysis and two-nodal analysis are performed using Fortran programs and multi-nodal analysis is carried out by Thermal Desktop for thermal design. One and two-nodal analysis decide optical properties of each surface and thermal conductivity between inside structure and outside structure. As a result, optic properties are decided that the outer surface of outside structure is alodine 1000, and the inner surface of outside structure and the surface of inside structure are black anodized. These analyses decide that GFRP is inserted between the outside structure and the inside structure, and thermal conductive sheet "DENKA BFG20" is inserted between each component and the surface mounted on it. Thermal Desktop calculates temperatures of components on HODOYOSHI-1. Optical property of-X panel is modified from alodine 1000 to white anodized. GFRP is inserted between the battery and the surface mounted on it. The result of these analyses shows that the temperatures of components are within the allowable temperature range. The thermal design of HODOYOSHI-1 have completed for 10 month. This thermal design is useful for the micro and nano satellites producing at a low cost and a short duration.
