Overview: Space gravitational wave detection missions typically consist of three identical satellites, with two laser links between the satellites at an angle of sixty degrees forming a Michelson interferometer. The arm length changes are measured using high-precision inter-satellite laser interferometry. As a key component of the inter-satellite laser interferometry system, the telescope system needs to have picometer-level optical path stability, a wavefront error of λ/30, and stray light less than 10^?10 of the transmitted power. To meet the requirements of space gravitational wave detection for the telescope system, an optical and mechanical integrated analysis and optimization method is proposed to design and optimize the primary mirror and its supporting structure. The off-axis parabolic primary mirror adopts the side three-point support method, and the influence of the support point position on the mirror surface shape and the rigid body displacement under gravity conditions has been studied. Optimization of the size of the triangular lightweighting holes on the primary mirror has been performed, and density-based topology optimization has been used to optimize the support backplate while ensuring that the first-order mode of the primary mirror component remains essentially unchanged. The flexural matrix of the primary mirror component supported by a parallel bipod linkage structure was derived based on spinor theory, and an evaluation function for the support structure was established. The size parameter range of flexible support was preliminarily determined by Matlab analysis. A optical-mechanical integrated simulation platform is set up to optimize the parameters of the support structure using a weighted sum method to convert the multi-objective optimization problem into a single-objective optimization problem. The results showed that the first-order frequency of the primary mirror component system was 392.43 Hz. Under gravity and temperature loads, the deformation of the primary mirror surface was better than λ/60, the translational rigid body displacement was better than 2.5 μm, and the rotational rigid body displacement was better than 0.5 μrad, all of which met the design specifications. Under space thermal disturbance of 10 μK/Hz^1/2, the size stability of the primary mirror component, represented by the displacement of the central point of the mirror, was at a level of 10 pm/Hz^1/2.

为减小无拖曳卫星的残余姿态误差，设计了一种基于动量交换的指向稳定性调控机构。采用复合轴控制的原理，与无拖曳姿态控制回路相配合，可将卫星的指向稳定性精度提高到纳弧度量级，同时减少工质损耗，达到延长卫星寿命的目的。利用压电陶瓷设计了一套敏感轴动量交换机构，并基于卫星姿态动力学对小质量块运动所产生的附加干扰力矩进行推导和分析。分别对复合轴系统的主轴系统和子轴系统进行整定，计算出满足性能需求的系统带宽。采用前馈逆模型和自适应PID控制对压电陶瓷的非线性和卫星所受扰动进行补偿。最后，通过Adams和Simulink联合仿真验证系统整体的可行性。仿真结果表明：该机构的介入可以有效降低控制系统带宽，实现10 nrad·Hz^-1/2@1 mHz~1 Hz的指向稳定性控制。

拼接镜面技术是光学合成孔径望远镜的三种实现方式之一，是未来大口径望远镜的重要研究方向。由于拼接镜面主动控制系统直接影响拼接镜面等效大口径镜面的光学性能，本文着眼于地基大口径望远镜的拼接镜面主动控制技术，由地基拼接镜面望远镜的发展过程展开，阐述拼接镜面主动控制系统的主要结构，对国内外拼接镜面主动控制系统发展概况进行分析和总结。归纳了拼接镜面主动控制系统实现主动调整和主动保持的关键技术，明确了深度学习理论在闭环控制，共相检测与校正和系统级仿真建模技术中的逐步应用和未来发展方向，为国内下一代地基大口径望远镜拼接镜面的控制方案设计提供相应的指导。