为提高设计效率提出了一种空间光学遥感器柔性支撑参数化设计方法。分析了温度变化、装配误差两种工况下对柔性支撑形变的需求。并根据折衷规划理论设置柔性支撑的优化函数，以某空间光学遥感器主镜所用柔性支撑为例给出柔性支撑参数化设计的详细设计过程。经过参数化设计，主镜柔性支撑基频达到88.8 Hz，温度变化4 ℃，镜面的均方根（RMS）达到5.3 nm， 0.1 mm装配误差下的镜面RMS达到12.9 nm，光轴水平1 g重力镜面RMS达到5.0 nm。柔性支撑的性能显著提高并且所有设计满足指标。同时设计过程实现了计算机自动化设计，大大减少了人力投入，缩减了设计周期。

A parametric design method for flexure supporting of the optical space remote sensor is presented to raise the design efficiency. The demands of flexure supporting deformation in the cases of temperature changes and assembly error are analyzed separately. The compromise programming method is used to establish optimal function of flexure supporting. Taking the flexure supporting used in the primary mirror of optical space remote sensor as example, the parametric design is provided in detail. After parametric design, the fundamental frequency of the flexure supporting is 88.8 Hz, the root mean square (RMS) of the mirror surface is 5.3 nm, when the temperature rise 4 ℃. The RMS is 12.9 nm when the assembly error is 0.1 mm, the RMS is 5.0 nm when 1 g gravity worked. The performance of flexure supporting significantly develops and all the design meets the targets. Computer automation design is applied during the design process, which greatly reduces the investment of human beings and the cycle of design at the same time.