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The thermal model describing the steady-state temperature state of the aluminized polymer spherical shell for the calibration spacecraft located in the shadow part of the Earth orbit is constructed. This model takes into account transfer of the thermal energy in the shell cavity by means of radiation and allows us to formulate the dependence of the temperature distribution over the shell surface on the spacecraft height above the Earth and on the radiation coefficients of the outer and inner surfaces of the shell. The quantitative analysis of the obtained dependence showed that when the mentioned radiation coefficients were increased, the temperature distribution would equalized over the shell surface. At the same time, the isothermal section of the shell with the lowest temperature located on the opposite from the Earth side of the shell was remained. When the spacecraft height above the Earth increases the area of isothermal section will increase, too, and a significant reduction of the average temperature will have place. This fact must be considered when estimating the availability of the used polymer material of the shell.

Simulation of the temperature state of the spacecraft shell in the shadow part of the orbit