论文部分内容阅读
含有多种功能开孔的轻质回转壳结构是航空航天结构系统内的常用支撑构件,其开孔形状直接影响结构的静动态性能。以回转壳结构为对象,基于超椭圆方程和坐标映射变换推导了回转壳开孔边界的参数化表达,开展了开孔形状动力学优化研究。为提高结构优化计算的精度、效率和收敛性,提出了准等弧长方法和基于均匀设计的序列响应面近似建模方法(SRSM),以分别实现空间超椭圆曲线的精确逼近、减少结构有限元分析成本和加快迭代收敛。以非支配排序遗传算法II(NSGA-II)作为响应面模型求解算法,结合有限元分析构建了回转壳开孔形状优化设计流程,开展了最大化结构一二阶频率带隙的典型回转壳结构开孔形状优化设计。结果表明,基于超椭圆方程和序列响应面法的开孔优化方法获得了有效改进结构动态特性的回转壳开孔形状,对开展计算耗时工程结构形状优化设计具有一定应用价值。
The lightweight revolving shell structure with multiple function openings is a commonly used support member in the aerospace structural system. The shape of the perforated hole directly affects the static and dynamic performance of the structure. Based on the hyperelliptic equation and the coordinate mapping transformation, the parametric expression of the open shell boundary of the shell was derived and the dynamic optimization of the shape of the open hole was carried out. In order to improve the accuracy, efficiency and convergence of structural optimization calculation, quasi-arc-length method and serial response surface approximate modeling method (SRSM) based on uniform design are proposed to realize the exact approximation of space hyperelliptic curves and to reduce the finite structure Meta-analysis costs and speed up iterative convergence. The NSGA-II algorithm was used to solve the response surface model, and the optimal design flow of the shell shape was established based on the finite element analysis (FEA). The typical shell structure of the first-order frequency bandgap Hole shape optimization design. The results show that the opening optimization method based on hyperelliptic equation and sequence response surface method can obtain the shape of the opening of the rotating shell which can effectively improve the dynamic characteristics of the structure, which has certain application value for the optimization design of the time-consuming engineering structure shape.