设计并研制了碳纤维复合材料主次镜连接筒.根据光学设计中的公差分配, 结合复合材料层合板理论, 分析了复合材料铺层设计对面内刚度和轴向及周向热膨胀系数的影响, 确定了最终的铺层方式.利用有限元软件分析了重力作用下及温度变化时主次镜间的位置变化及连接筒的模态分布.最后, 完成了碳纤维复合材料薄壁连接筒的成型和精加工, 检测了主次镜系统光学性能, 并对装配完成后的相机进行了鉴定级力学试验.分析结果表明: 在1g重力载荷及2℃温升耦合作用下,次镜偏心小于0.002 mm, 次镜倾斜小于2″, 主次镜连接筒及次镜系统组合体基频达到265 Hz, 满足光学设计要求和结构稳定性要求.光学性能检测结果及力学试验结果表明, 主次镜系统波像差满足装配要求, 主次镜连接筒能够承受鉴定级力学试验考核, 连接主次镜的两端响应放大仅1.7倍, 体现了良好的阻尼性能.本文中研制的主次镜连接筒重量仅为6.4 kg, 实现了高轻量化和高刚度, 满足空间相机对主次镜位置精度和稳定性的要求.

In this paper, a connecting barrel for space camera of Carbon Fiber-Reinforced Plastics (CFRP) is designed. Based on tolerance distribution in optics and composite lamination theory, the in-plane stiffness and thermal expansion coefficients due to lamination are analyzed, with structure optimized. Position error between primary and secondary mirrors, as well as modal distribution of the connecting barrel under gravity and temperature change are analyzed by finite element software. Finally, molding and fine tooling of the CFRP barrel is carried out, followed by optical inspection of the mirror system and appraisal mechanical test on the assembled camera. The analysis results show that the optical design and structural stability are satisfied by facts of 1) ＜0.002 mm eccentricity and ＜2″ tilt achieved on the secondary mirror under 1g gravity load and 2℃ temperature rise coupling; 2) 265 Hz fundamental frequency on the connecting barrel and on the secondary mirror combination system. Optical and mechanical performance tests show that the wavefront error of the primary and secondary mirror system meets the assembly requirements, and the barrel can bear the mechanical test of qualification level. The dual-terminal response of the barrel is amplified 1.7 times only, demonstrating desired damping property. The proposed barrel is merely 6.4 kg, which realizes light weight and high rigidity, thus satisfying the position accuracy and stability requirements on the primary and secondary mirrors for space cameras.