星载激光通信终端在轨机动对温度影响

对激光通信终端在轨瞬态温度变化开展了仿真，以期研究在轨机动的影响、热分析和热试验时机动模式的简化模拟。通过合理地分析与简化，建立终端的轨道热分析模型，准确模拟在轨机动，根据典型机动模式、外热流和涂层退化等因素设计了计算工况，得出了终端在轨运行过程中的温度场随时间和姿态变化规律。结果表明：不同机动模式下的温度变化存在差异，最大可达23.0℃，采用固定姿态或一维转动的简化热分析或热试验不能准确模拟实际飞行温度，甚至不能部分替代二维转动热分析或热试验；光学天线和反射镜的温度控制是制约终端工作的瓶颈，为终端设计合适的避光机动策略，可大幅度提高温度稳定度和均匀度。研究结果可以为光机电设备在轨机动策略的设计和改进提供参考。

Impact of In Orbit Maneuver on Temperature of Satellite Borne Laser Communication Terminal

 In order to study the influence of an in-orbit maneuver and the simplified maneuver mode in thermal analysis and thermal test, the simulation research is carried out to testify the transient temperature variations of a laser communication terminal. A thermal analysis model for terminals is established by means of the physical analysis and logical simplification. The model can accurately simulate an orbit maneuver. The calculation cases are designed according to the typical maneuver mode, heat flux and coating degradation. The temperature distribution variation on terminal with different attitudes and time of the ascending node are given. According to the analysis results, there is a temperature difference of up to 23.0 ℃ between the temperature changes of the different maneuver modes. The simplified thermal analysis and test of one-dimensional rotation and fixed posture can not accurately simulate the actual flight temperature, and even can not replace the thermal analysis and test of the two-dimensional rotation in part. The temperature control of the optical antenna and reflectors is a bottleneck restricting the work of the terminal. The temperature distribution variation can be availably reduced with terminal sunlight avoidance. The results could provide a reference for the design and improvement of the in-orbit maneuver strategy.