基于有限元法的空间遥感器主镜支撑位置优化

Optimization on primary mirror support position of space remote sensor based on finite element method

为更准确地设计空间遥感器主镜,以有限元法为基础,研究空间遥感器主镜在自重情况下引起的镜面面形变化情况,在主镜镜面面形符合实际工程要求的情况下,通过MSC Nastran进行优化处理并最终确定出主镜的最佳支撑位置,同时确定主镜轻量化结构.以主镜背部3个支撑孔中心坐标为设计变量,以主镜镜面变形最大值作为目标函数进行实例优化分析,并与传统经验法的计算结果进行对比,结果表明所采用的有限元优化方法具有较大的优越性,为某型空间遥感器的成功研制打下良好基础.

To achieve the more accurate design of space remote sensor, the primary mirror surface deformation affected by its self-weight is studied based on the finite element method. Under the fact that the shape of primary mirror meets the requirements of actual engineering, optimization is processed by MSC Nastran, the best primary mirror support position is finally determined and the primary mirror lightweight structure is identified. An example of optimization analysis is given, in which the coordinates of three support center at the back of primary mirror are taken as design variables, and the maximum deformation value of primary mirror is taken as objective function. The comparison of the results obtained by the example and the traditional calculation method indicates that the optimization based on the finite element method has better advantages, which lays a good foundation for the development of a space remote sensor.