Thermal effect of radiation of high-temperature engine on docking mechanism at space station tail

The physical and mathematical models were presented for thermal analysis of the combined system according to the geometrical characteristics of engine group and docking mechanism at the space station tail and the thermal network theory of spacecraft. The thermal effect of engine radiation at high temperature on docking mechanism was put emphasis on. It is shown from the calculational results that the circular range in which thermal effect works is from θ=90±30 to θ=270±30. Emissivity is an important factor that will influence the temperature of docking mechanism. In the course of changing the orbit the circular temperature difference and maximum temperature of docking frame both reach 90C, moreover, the absolute temperature amplitude comes to 83C, which are all in excess of acceptable value and will threaten the movement and fixation functions. So the effective thermal control measures should be adopted.