论文部分内容阅读
本文运用了结合混合元胞自动机(Hybrid Cellular Automaton,HCA)方法和基于LS-DYNA显式有限元算法的动力学拓扑优化方法来解决非线性动力学拓扑优化问题,并形成了该方法迭代过程的数学模型.运用该方法,对某航空发动机叶片进行了动力学拓扑优化设计,给出了优化后结构的材料分布,并与优化前结构进行了对比分析.结果表明,优化后结构相比于优化前在材料分布上更加合理,在减少质量的同时降低了结构在冲击过程中的最大应力,实现了航空发动机的抗冲击优化,为航空发动机动态优化设计提供了有效分析方法.
In this paper, hybrid Cellular Automaton (HCA) method and dynamic topology optimization method based on LS-DYNA explicit finite element algorithm are used to solve the nonlinear dynamic topological optimization problem, and the iterative process The mathematical model of aeroengine blades was optimized by using this method, the material distribution of the optimized structure was given and compared with the pre-optimization structure.The results showed that compared with the optimized structure, Optimized before the distribution of materials more reasonable, reducing the quality of the structure while reducing the maximum stress in the impact process to achieve aeroengine impact resistance optimization for the dynamic optimization of aeroengine design provides an effective analysis method.