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.

全景环带光学系统凭借周视范围实时成像的特点已在超大视场光学领域中得到了广泛应用。传统的全景环带光学系统将折射、反射面集成在一片块状透镜中，光线在其内部进行多次折、反射导致头部单元体积较大，同时红外透镜材料密度大、折射率温度稳定性差等特点也与光学遥感器轻量化、可靠性高的应用需求相矛盾。文章基于像差理论，讨论了全景环带两反射镜红外光学系统头部单元初始结构设计方法，将Q型（Q-Type多项式）非球面引入全景头部单元增加优化变量，用偏离因子因子${k_{{\text{RMS}}}}$数值表征非球面加工难度，设计了以两反射镜为头部单元的全景环带红外光学系统。该系统在奈奎斯特频率（20线对/mm）处调制传递函数优于0.5；全视场像元（25 μm×25 μm区域内）能量集中度优于65%，像质评价结果表明其成像品质良好。该设计在缩小系统体积、提高光学设计优化效率方面有很大的改进，满足超大视场实时成像的应用需求。