空间长条形反射镜背部三支撑点的设置

Position layout of rear three point mounting for space rectangular mirror

采用背部三点支撑方式的空间光学遥感器长条形反射镜目前尚无普遍适用的支撑点设置方法,只能对某一确定尺寸和长宽比的反射镜进行专门设计。本文提出了基于规则模型的、以参数化模型为核心的集成参数化设计方法,并建立了长条形实体反射镜背部三点支撑集成参数化模型。在集成环境中通过试验设计、响应面分析等方法对设计参数进行了分析和优化,结果表明在轴向重力工况,镜面面形峰谷(PV)值优于λ/10(λ=632.5nm)的设计要求下,长条形碳化硅反射镜背部三点支撑的最大适用尺寸为1m。文中给出了最优支撑点布置,并确定了厚径比最优为1/10。最后,对集成参数化分析方法进行了精度分析,结果显示该方法整体误差为6.13%。提出的方法确定了空间长条镜背部三点支撑的适用范围,提供了支撑点最佳布置,为空间相机不同尺寸要求的长条镜设计打下了基础。

It is difficult to conclude a general method in opto-mechanical design for rectangular mirrors mounted via rear three-point method in a space remote sensor. So, the individual opto-mechanical design for a given size rectangular mirror is usually used. In this paper, an integrated parametric design method based on a regular model was proposed and a parametric model for 3-point mounting space rectangular mirror was established. Integrated analysis and response surface method were used in analysis and optimization of the designed parameters. The results show that the size limit of mirror for rear three mounting method is 1 m for the requirement of the axial self-weight deflection of wavefront error less than 1/10A （A=632.5 nm）. The best mounting position was proposed, and the proper thick aspect ratio was given by 1/10. The accuracy of the proposed integrated parametric design method was analyzed, and the results show that the total analysis error is 6.13%. The method defines the proper size of rectangular mirror with rear three point mounting, gives the best mounting position and provides a standard for design of space remote sensors.