介绍了下一代空间望远镜的可展开式反射镜的概念及设计方案，分析了展开式反射镜单元镜的支撑方案，目的是确定单元镜支撑点数量及排布方式。用有限元方法分析了12－6－1、12－8－1和16－8－1型三种支撑点排布方式下各自的镜面自重变形。计算结果表明，采用16－8－1型的排布方式较为合理。计算带有支撑座的单元镜在1g惯性载荷作用下，通过调节支承座位移，获得镜面RMS值为16．52nm，小于1／4波长(632．8nm)的面形，表明将该支撑方案应用于单元镜具有可行性。

The concept design and progress of deployable unit mirror about next generation space telescope was described.Some schemes about deployable mirror were introduced. The finite element method was used to analyze the unit naked mirror and some different mirror support schemes. The principal aim of the naked mirror analysis was to get numbers of support points and the ways of the support. There were three schemes including 12-6-1,12-8-1 and 16-8-1models. Deformation of deadweight was calculated under the three conditions. The way of 16-8-1 was more suitable than the designs of other two. The optimum design of the support structure was based on the surface figure error and structure rigidity. Support subassembly was amended to meet with the mirror surface RMS in the range of 30 μm. Deformation of the mirror with support structure was calculated. The result is 16.52nm,lower than a quarter of the wavelength,which indicates the feasibility of the support scheme applied to unit mirror.