Abstract: In view that there is no traditional heat dissipation surface for micro-satellites with frame hollow-out structure, a thermal control design method for micro-satellites under constraints of extremely low cost and low weight was proposed in this paper. A flexible thermal conductive channel was constructed by attaching low-cost industrial grade carbon nano-copper foil between the equipment and the satellite structure. A germanium coated polyimide film was fastened on the outer side of the hollow-out structure to take advantage of the infrared transmittance of the film to radiate part of the heat of the equipment to the deep space cooling background. The in-orbit telemetry data of Yangwang-1 satellite with application of the proposed method shows that the temperature of the entire satellite equipment is 13 ℃ to 30 ℃, meeting the design index requirements. The proposed method may provide a reference for the thermal control design of similar hollow-out structured satellites.