空间站空空支架天线热设计与仿真分析

为研究核心舱飞行姿态、空间外热流、核心舱发动机羽流参数以及天线外表面热控涂层对空间站空空支架天线温度的综合影响，验证天线被动热控设计的有效性，进行了2种低温工况和6种高温工况的热分析。结果显示:低温工况下，通信天线惯性飞行时的最低温度低于正向飞行时的；展开臂多层表面最低温度为-85 ℃，满足温控指标。高温工况下，通信天线惯性飞行时的温度高于正向飞行时的；轨控发动机的羽流热效应大于偏航发动机的。通信天线内外表面均喷涂ACR-1温控白漆，1倍轨控发动机羽流热流密度时，最高温度为123 ℃，可满足实际使用要求。

Thermal design and simulation analysis of space frame antenna used on China’s space station

To study the comprehensive thermal effects of the flight attitude, the external thermal flux, the plume parameters of the core module engine, and the thermal control coatings outside the antenna on the antenna temperature, a thermal analysis is conducted under two low- temperature conditions and six high-temperature conditions to validate the thermal design. It is shown that under the low temperature conditions, the minimum temperature of the space frame antenna in the inertial flight mode is lower than that in the forward flight mode, while the minimum temperature of the multi-layer surface on the deployable manipulator is -85 ℃, which meets the requirements of the thermal control. Under the high temperature conditions, the antenna temperature in the inertial flight mode is higher than that in the forward flight mode; the thermal effect caused by the plume of the orbit control thruster is greater than that caused by the yaw thruster. When the internal and external surfaces of the communication antenna are coated with the ACR-1 white paint, and with one time plume heat flux density of the orbit control thrusters, the maximum temperature of the antenna is 123 ℃, not exceeding the requirements for the usage.