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.

储存环机械支撑的静力变形、调节精度决定各物理元件的定位精度，其动态响应特性间接影响着束流的稳定性，机械支撑是各物理元件的安装基础，保证磁铁、真空室、束测元件正确的安装、运行，发挥出相应的物理性能。主要从支撑的静力变形和固有频率两个方面对机械支撑进行优化设计。以深圳产业光源（SILF）共架支撑为例，利用SolidWorks和Ansys软件对储存环磁铁机械支撑进行设计、拓扑优化。详细阐述了储存环机械支撑设计、优化的过程，并将最终优化完成的支撑模型与磁铁模型进行装配，在尽量接近真实工况的基础上对整体支撑进行仿真计算，以确保支撑整体能够达到设计指标。

主、次镜支撑技术是共光路光学系统的关键技术之一。针对在±60℃温度变化范围内工作的机载共光路光学系统，根据热膨胀系数匹配原则分别选择殷钢和ULE、钛合金和K9配对作为主、次镜及支撑结构的材料，并设计了高刚度无热化柔性支撑结构。最后，利用自研的光机联合仿真程序对主、次镜面型及整个光学系统的成像质量进行了光机一体化分析。分析结果表明：殷钢和ULE配对时，在±60 ℃均匀温差和10 ℃轴向、径向温度梯度下，主、次镜去除离焦后面型优于（1/100）λ，整个光学系统点列图RMS半径小于艾里斑半径，相面中心波前优于（1/50）λ，MTF@63 lp/mm优于0.45，无热化柔性支撑的一阶固有频率高达263 Hz；钛合金和K9配对时，60 ℃均匀温差下系统成像指标满足使用要求，10 ℃轴向、径向温度下成像质量无法满足使用要求。对装调完的殷钢和ULE配对光机系统进行了低温下分辨率测试，分辨率无明显变化，说明设计及分析可行。

为了保证平背伺服摆镜的镜面精度和支撑刚度，设计了一种周边柔性支撑的方案，通过对摆镜与镜座粘接处机械结构进行切口处理形成铰链结构，降低结构刚度，减小结构变形产生应力的影响。由于摆镜形状、粘接点位置、柔性支撑结构参数较多，并且相互耦合，首先采用正交实验法对摆镜主要参数进行分析与优化，确定摆镜形状尺寸参数和粘接点位置，随后优化设计摆镜柔性支撑结构。仿真分析和实验表明，采用该周边柔性支撑后，摆镜组件一阶频率为446.66 Hz，在±5 ℃温升（温降）和标准地球重力共同作用下，最大面形误差RMS为λ/42.87，能够满足动、静态刚度和热尺寸稳定性要求。随后使用 ZYGO 干涉仪在 (23±5) ℃ 温度范围内对加工装配后的摆镜面形进行检测，结果表明，摆镜面形PV值优于λ/5.1，RMS优于λ/43.28，满足 RMS≤λ/40的指标要求。实验结果表明，柔性支撑参数设计可靠，满足使用要求。