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为了确保成像质量,空间光学遥感器反射镜既要满足在重力和温度耦合的复杂工况下面形误差的要求,同时还应具有良好的动态特性。设计了一种圆形小型反射镜,并类比反射镜径向挠性安装原理设计其柔性支撑结构。采用CAE有限元分析软件对该反射镜的柔性支撑结构的参数进行了优化,最终确定了一种合理的柔性支撑结构。经过分析计算,该柔性支撑结构能满足在重力和温度耦合的复杂工况下反射镜面形误差小于λ/50(λ=0.6328μm)的要求,反射镜组动态特性良好,一阶模态大于280Hz。
In order to ensure the image quality, the space optical remote sensor mirror must meet the requirements of the form error under the complex conditions of gravity and temperature coupling, and should also have good dynamic characteristics. A circular small mirror was designed and the flexible supporting structure was designed based on the radial flexible installation principle of the analogue mirror. The parameters of the flexible support structure of the reflector were optimized by CAE finite element analysis software, finally a reasonable flexible support structure was determined. After analysis and calculation, the flexible support structure can meet the requirements of the mirror surface shape error less than λ / 50 (λ = 0.6328μm) under the complicated working conditions of gravity and temperature coupling. The mirror group has good dynamic characteristics and the first order mode is more than 280Hz .