Abstract：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.
康永刚，李春生，陈希多,罗群，党晓娟. 航空大壁板装配连接局部变形数值建模与仿真分析[J]. 航空制造技术, 2020, 63(3): 45-52.
KANG Yonggang, LI Chunsheng, CHEN Xiduo, LUO Qun,DANG Xiaojuan. Numerical Modeling and Simulation Analysis of Local Deformation for Aircraft Large-Walled Panel Assembly Connection. Aeronautical Manufacturing Technology, 2020, 63(3): 45-52.
2020, 
