Aircraft large-walled panel is an important component of the aerodynamic shape of the aircraft. It has the characteristics of large size and weak thin wall. It is easy to produce assembly deformation during the automatic drilling and riveting assembly process

including the overall bending and torsion deformation of panel and the peripheral defects of rivet. In this paper

a large-walled panel test shows a local subsidence deformation along the long axis. The deformation problem is complicated and directly affects the subsequent assembly process. It is a problem about how to achieve strong coupling among the automatic drilling and riveting process

the rivet and its elastoplastic deformation of the connected parts. For the deformation problem

based on the constructed automatic drilling and riveting process model combined with finite element numerical simulation analysis

the simulation prediction of the structural deformation of the typical aircraft panel with multi-nail riveting assembly is carried out. Through the discussion and analysis

the process factors leading to a local deformation problem are given

which provide a theoretical basis for the optimization of the aircraft panel automatic drilling and riveting process

and the effectiveness of prediction model is verified by comparison with the experimental results.