在保证“一对多”激光通信终端光学天线的成像质量前提下, 为解决光学天线两端面承担载荷的技术问题, 提出了一种用于卫星平台的可承载式激光通信光学天线。对主镜组件、可承载式遮光罩及次镜支撑桁架的结构形式以及连接方式进行正对性设计, 保证主镜面形精度以及次镜的位置精度。使用ANSYS有限元分析软件进行分析, 结果表明: 整机一阶模态151.54 Hz; 光学天线前端可承载8.5 kg, 后端面可承载13 kg; 径向1 g自身重力及两端承载工况下, 主镜面形精度RMS值(均方根误差)为λ/158、PV值(最大峰谷误差)λ/30, 次镜最大倾角1.88″; 在(20±5)℃环境温度、轴向1 g自身重力及两端承载工况下, 主镜面形精度RMS为λ/65、PV为λ/14, 次镜最大倾角1.21″, 该天线承载后具有较好的力、热稳定性以及成像质量, 可以满足天线在地面装调、检测以及发射过程中的指标要求。采用质量块模拟两端负载质量及重心位置, 使用ZYGO干涉仪进行测试, 结果表明系统波相差能够满足1 g重力及负载条件下, 系统波相差RMS值优于λ/15的指标要求。

In order to solve the technical problem of bearing load on both ends of the optical antenna, a loadable laser communication optical antenna for satellite platform was proposed, and at the same time guaranteed the imaging quality of the one point to multi-point laser communication terminal optical antenna. In order to ensure the surface accuracy of the primary mirror and the position accuracy of the secondary mirror, the structure and connection form of the primary mirror assembly, the loadable baffle and the secondary mirror support truss were optimized. Using ANSYS finite element analysis software for analysis, the results show that the first-order mode frequency of this structure is 151.54 Hz; The front end of the optical antenna can carry the quality of 8.5 kg and the rear end of the antenna can carry the quality of 13 kg; Under the condition of 1 g radial self-gravity and bearing load at both ends, the RMS(root mean square error) value of surface shape error of the primary mirror is λ/158, PV(maximum peak-to-valley error) value is λ/30, the maximum inclination of the secondary mirror is 1.88″; Under the condition of (20±5)℃ ambient temperature, 1 g axial self-gravity and bearing load at both ends, the RMS of the primary mirror is λ/65 and the PV is λ/14, the maximum inclination of the secondary mirror is 1.21″. It shows that the antenna has good mechanical properties, thermal properties and imaging quality after being loaded. It can meet the requirements of the antenna in the installation, detection and transmission of the ground. The ZYGO interferometer was used for testing. The quality of the load and the position of the center of gravity were simulated by the mass. The results show that the system wavefront aberration of the system RMS can meet the index requirements of λ/15 under the condition of 1 g gravity and load.