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根据柔性机翼前缘的变形要求,以离散体结构拓扑优化为出发点,以实际位移与目标位移之间的偏差为目标,建立目标优化函数。采用类树形结构的载荷路径建立初始构形,利用遗传算法(GA)进行结构拓扑优化,并结合拓扑结构优化结果进行二次优化,获得更优解。通过ANSYS仿真分析,结果表明该方法是可行的。
According to deformation requirements of the leading edge of flexible wing, taking the topological optimization of discrete structure as the starting point, the objective optimization function is established based on the deviation between the actual displacement and the target displacement. The initial configuration was established by loading path with tree-like structure. The genetic algorithm (GA) was used to optimize the structure topology, and the second optimization was made based on the topology optimization results to obtain a better solution. By ANSYS simulation analysis, the results show that the method is feasible.