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为了降低航空光电侦察设备的整体质量,减小反射镜在复杂航空环境下的面形变化,利用有限元方法对某长条形反射镜组件结构进行了优化。首先,计算轻量化反射镜所需的支撑点数量,并对支撑点的位置进行优化。接着,为了解决温度变化时组件材料线胀系数不匹配带来的热变形问题,在支撑结构中引入了柔性铰链,并对柔性铰链参数进行了优化。最后,对反射镜组件进行面形精度分析,得到反射镜RMS为20.3 nm,小于1/30λ(λ=632.8 nm);对组件进行模态分析及试验,得到一阶固有频率分别为138 Hz和162 Hz,满足设计指标要求,分析及试验结果表明了该反射镜的支撑结构合理可行。
In order to reduce the overall quality of the aeronautical reconnaissance equipment and reduce the shape change of the mirror under complicated aviation environment, the structure of a long strip mirror assembly is optimized by the finite element method. First, calculate the number of support points required for a lightweight mirror and optimize the position of the support points. Then, in order to solve the thermal deformation caused by the mismatch of linear expansion coefficients of the component materials during the temperature change, a flexible hinge is introduced into the supporting structure and the parameters of the flexible hinge are optimized. Finally, the surface accuracy of the mirror assembly was analyzed to obtain a mirror RMS of 20.3 nm, less than 1 / 30λ (λ = 632.8 nm); modal analysis and testing of the module, the first natural frequency were 138 Hz and 162 Hz, meet the design requirements, analysis and test results show that the mirror support structure is reasonable and feasible.