无论是在地基成像系统中还是太空望远镜中，轻质镜以其重量轻、刚度大的优点已经得到广泛的应用，然而镜子发射到太空后由于太空环境下温度变化和重力卸载等因素，造成镜面面形变差。为了解决这一难题，设计了一种新型的用于空基成像系统的轻质能动镜，在发射太空后能够校正自身变形。采用该轻质能动结构可以使主镜口径做到更大，从而提高分辨率和灵敏度，同时能够实现在轨改变镜面面形，将镜面的面形控制在光学误差内。采用拉丁超立方采样和全因素搜索优化算法，结合参数化有限元建模，对能动镜进行了结构优化设计，得到了筋板厚度、镜面厚度、驱动器长度、底座高度对离焦拟合误差和拟合离焦最大峰谷值的影响趋势。这对于未来针对特定任务的设计有一定的参考价值。

Whether in earth imaging systems or in astronomical telescopes, lightweight mirrors have been used widely because of its light weight and good stiffness. However, the initial surface shape of mirrors will be aberrated after sending to the space, due to the effects such as gravity release, thermal changes in the space and so on. To solve the problem, a new type of lightweight, active primary mirrors capable of adjusting their shapes after launch, is designed for using in space-based imaging systems. This enables primary aperture larger to improve resolution and sensitivity, which is capable of on-orbit surface shape correction to control the shape of the mirrors to optical tolerances. Latin hypercube sampling and full factorial search algorithm is used for optimization of the mirror design, combined with the parameterized finite element mirror model. The trend of effects of rib thickness, face sheet thickness, actuator length, substrate height on fitting error and maxium peak to valley value is acquired. These results are meaningful to design that perform well with respect to specific missions in the future.