Panel is an important component of keeping aerodynamic shape in the aircraft. To ensure the flight performance 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 riveting 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.