The objective of this article is to examine potential techniques for suppressing solar heat flow on the optical antenna of a laser communication sensor. Firstly, the characteristics of the geosynchronous Earth orbit’s (GEO) space radiation environment are analysed, and a combined passive and active thermal control solution is proposed. Secondly, the temperature distribution of the lasercom sensor under extreme operating conditions is simulated utilising IDEAS-TMG (6.8 NX Series) software, which employs Monte Carlo and radiative heat transfer numerical calculation methods. Finally, a strategy for avoiding direct sunlight around midnight is proposed. The simulation results demonstrated that the thermal control solution and solar avoidance strategy proposed in this paper achieved long-term fine-stable control of the temperature field of the optical antenna, which met the thermal permissible communication hours per daily orbit cycle in excess of 14 h per day.

针对激光通信与测距一体化星间链路载荷轻小型单反射镜组件进行结构设计与力热稳定性研究，开展单反镜柔性支撑机构优化设计，根据运载力学环境与在轨力热环境工况，对反射镜组件进行光机集成分析，验证光机结构的在轨力热稳定性.分析结果表明，双层圆弧形槽口柔性支撑结构在温度拉偏后反射镜的面型精度均方根（RMS）可达λ/72，基频模态为417.93Hz，满足指标要求.进一步对反射镜组件进行动力学分析，随机振动分析结果表明，反射镜加速度响应均方根为11a_rms，满足3σ准则.通过0.2g正弦扫频试验验证了有限元模态分析相对误差为2.23%，实验结果表明，反射镜组件柔性支撑设计合理，力热稳定性分析结果基本准确可靠，满足工况要求.