Panel is an important component of keeping aerodynamic shape in the aircraft. To ensure the flight perfor-mance of aircraft, it is essential to improve the assembly accuracy of the panel's boundary dimensions. However, the traditional study mainly focused on the deformation analysis of the rivets and rivet holes, and the effect of riveting process on the global deformation was seldom considered. In this paper, the panel's automatic drilling and riveting was taken as the object of study, and a solution of acquiring deformation, namely "local-global" method, was proposed based on the single-rivet FE model. The solid elements are used in the adjacent regions of rivet hole, and the shell elements are used in the remaining regions of the panel. By means of the linking method of solid element and shell element, the "local-global" mapping model was established. Using this model, the complex stress-strain appearance around the rivet hole was transferred to the shell element in a relatively simple state by the solid element, which improved the computational efficiency. The numerical simulation of large panel rivet-ing deformation was also realized. Finally, in order to minimize the maximum riveting deformation, the genetic algorithm was used to optimize the riveting sequence. And the result showed that the deformation has been effectively controlled.%壁板是构成飞机气动外形的重要组件,提高其外形装配精度对保证飞机的飞行性能至关重要.传统的研究主要集中在铆钉及孔周围的变形,而对壁板铆接整体变形的研究较少涉及.以壁板自动钻铆为对象,以单钉铆接变形分析为元模型,提出了壁板铆接"局部-整体"变形快速求解方法.钉孔周围采用体单元,壁板其余部分采用壳单元,利用"体-壳"连接建模方法,构建了"局部-整体"映射加载模型,将钉孔周围复杂的应力应变状态传递到壁板整体薄壳模型上,实现了壁板铆接变形的快速计算;以铆接变形最大值最小为目标,采用遗传算法进行铆接顺序优化,实现了对壁板铆接变形的有效控制.
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