The aviation large panel is an important component that constitutes the aerodynamic shape of the aircraft. It has the characteristics of large size, thin wall and weak rigidity. It is prone to produce assembly deformation during the automatic drilling and riveting assembly connection process, including the overall bending and torsion deformation of the panel, and the defects around the rivet. In this paper, through the test of automatic drilling and riveting assembly of large panels, a local sinking deformation along the axis of the long stringer is found. The cause of this deformation problem is complex and directly affects the subsequent assembly process. It is a strong coupling problem between the automatic drilling and riveting process and the elastic-plastic deformation of the rivet and its connected parts, and it has a high correlation with the meso-structure of the plate structure around the nail hole after the rivet is riveted.Aiming at this deformation problem, this paper first established a process model of the riveting process and designed riveting test pieces with different process parameters. The effects of pressure riveting force, upsetting riveting process time, upsetting riveting residence time and upper riveting head cavity on the meso-structure of the riveting area are explored, and the correlation between the meso-structure of the riveting area and the riveting process parameters is analyzed. Then, based on the above research, a finite element numerical model of a typical aircraft siding riveting component structure including meso-structure is established. Through the finite element simulation calculation of the model, the coupling relationship between macroscopic deformation and mesoscopic structure is further explored. Finally, a finite element model of large panel riveting is established to verify the existence of local subsidence and deformation along the axis of the long truss, and combined with the meso-structure, the optimal process parameters are given.The research results of this paper are as follows. A kind of deformation defect caused by the automatic drilling and riveting process of aviation large panel is discovered along the axis of the long stringer. The influencing factors of the riveting process parameters on the meso-structure near the rivet hole and the coupling relationship between the meso-structure and the macro-deformation are explored, which provides a theoretical basis for the optimization of the automatic drilling and riveting process of aircraft panels. A finite element numerical model of a typical aircraft panel riveting component structure including meso-structure is established, and the simulation model is validated by comparison with the test results.

Optimization of Riveting Assembly Process Parameters for Aviation Large Panels Based on Mesoscopic Features

Paper Proceedings: https://asmedigitalcollection.asme.org/IMECE/IMECE2021/volume/85543

ASME 2021 International Mechanical Engineering Congress and Exposition (IMECE2021)

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