C/SiC在大口径空间望远镜次镜承力筒的应用

设计并研制了基于C/SiC复合材料的大口径空间望远镜次镜承力筒。首先对C/SiC复合材料的特性以及在空间遥感器领域的应用进行了介绍。其次以某大口径空间望远镜次镜承力筒为例，对不同材料下次镜承力筒的质量、力热性能进行了对比。仿真分析表明:设计的C/SiC复合材料次镜承力筒低至32 kg，相比钛合金筒减轻45.5%；基频为204 Hz，满足设计要求；更易于控制热变形对反射镜面形的影响。最终完成了C/SiC复合材料次镜承力筒的研制和主要物理性能的检测，并进行了力学振动试验考核，对振动前后结构的三坐标测量数据进行了比对。结果表明:次镜承力筒组件的基频良好，振动试验前后频漂低于1%，结构的微位移变化量级在微米级。为应用C/SiC开展空间遥感器大尺寸整体成型支撑结构的设计提供有效的参考价值。

Application of C/SiC to secondary mirror bearing cylinder in large aperture space telescope

C/SiC composite material was applied to design of secondary mirror bearing cylinder in large aperture space telescope. Firstly, the material characteristics of C/SiC composite material and the applications in space optical remote sensor were introduced. Secondly, taking secondary mirror bearing cylinder of a large aperture space telescope as an example, the weight and structural-thermal performance based on different materials were compared. The analysis results indicate that C/SiC reduces the weight of secondary mirror bearing cylinder to 32 kg by 45.5% compared with titanium alloy cylinder. With natural frequency of 204 Hz, the structure meets the design requirement and can control the influence of thermal deformation on the shape of mirror. Finally, the C/SiC secondary mirror bearing cylinder was developed and the main physical properties were tested, and the mechanical vibration test was carried out, and the three-coordinate measurement data of the structure before and after vibration were compared. The results show that the fundamental frequency is excellent. Moreover, the frequency drift is less than 1% before and after the vibration test, and the micro displacement of the structure is in micron level. This paper provides several reference value for the design of large size integral bearing structure of space remote sensor by using C/SiC.