Thermal control system design and thermal test of high-resolution space camera

This study introduces the design and test of the thermal control system of high-resolution space camera. To ensure thermal stability of the camera’s components, the thermal control system employs a predominantly passive thermal management approach, supplemented by active thermal control design. First, the structure, working conditions and the internal and external thermal environment of the camera are analyzed. Subsequently, a detailed design phase for the camera’s thermal control system was undertaken. The performance of the thermal control system design is preliminarily verified by thermal analysis simulations. Corresponding thermal balance test results demonstrated that both the primary and secondary mirrors maintained stable temperatures at approximately 20°C, the focal plane temperature is controlled at 0.49°C∼14.86°C, the radial temperature difference is less than 1°C, and the temperature of two electric boxes is controlled at -3.59°C∼27.04°C, indicating that the thermal control system has resistance to external thermal influence, good heat dissipation capabilities and can provide temperature compensation. This study provides a valuable thermal management methodology for space cameras operating under extreme thermal conditions, offering significant contributions to the advancement of spacecraft thermal control techniques.