Hybrid Modeling Method for the Complex Radiative Cooling Network in the Chinese Space Station

Thermal analysis of spacecraft involves complex heat flux outside space and heat transfer calculation of equipment inside space, which is the basic guarantee of its long-term stable operation. In this paper, the core module of the Chinese Space Station is taken as an example to conduct hybrid modeling of its complex radiation and heat dissipation network. The external heat flux received by spacecraft is affected by many factors, such as its attitude, orbit parameters, and solar orientation. First, based on the defined reference coordinate system, the whole station is divided into eight quadrants. Then, an intelligent occlusion algorithm is proposed to solve the complex occlusion relationship according to the space quadrant method and fuzzy logic, and then the external heat flux is obtained. Finally, the dynamic response of the station under different conditions is studied by combining traditional mechanism modeling and an intelligent algorithm, and the maximum heat dissipation capacity was obtained. The results show that the temperature control valve opening will seriously affect the main flow of the loop, and the maximum difference can be 0.1 kg/s. In addition, the external heat flux changes periodically, so that the flow of each branch and the valve opening also changes periodically. In the sunlight area, the radiator receiving the external heat flux is about 77,000-90,000 W, and the maximum heat dissipation capacity is 12,000 W. Those values are 28,000 W and 22,000 W, respectively, in the shadowed area. Moreover, the hybrid modeling method proposed in this paper has an important reference value for spacecraft thermal analysis and research in other fields.