Analysis of Residual Stress and Fatigue Performance of Al-Li Alloy Riveted Panel
As a new light alloy material,Al-Li alloy has been widely used in the manufacture of aircraft skin wall panel and other structures.The aircraft skin and wall panel are connected by automatic riveting,and the distribution of residual stress around the rivet hole after the riveting process is closely related to the fatigue performance of the riveting structure.In this study,the finite element model of the press riveting process of the 2060-T8 Al-Li alloy plate was established by ABAQUS software.It is found that the residual stress on the wall of the rivet hole after riveting decreases from the place close to the rivet head to the place close to the rivet head.With the pressure riveting force increasing from 28.5 to 46 kN,the average residual stress of the hole wall of the riveted plate with the rivet material of 2117-T4 is increased by 0.33 times,and the uniformity of the residual stress distribution along the thickness of the wall plate is increased by 1.8 times.The average residual stress of the hole wall of the riveted plate with 7050-T73 rivet material is increased by 0.58 times,and the uniformity of the residual stress distribution along the thickness of the wall plate is increased by 1.84 times.The fatigue crack originates near the hole wall of the riveted lower plate.With the increase in the riveting force from 32.5 kN to 42 kN,the fatigue life of the riveted plate with the rivet material of 2117-T4 is increased by 0.31-0.80 times,and the fatigue life of the riveted plate with the rivet material of 7050-T73 is increased by 0.06-1.61 times.Compared with the riveted plate with rivet material of 7050-T73,the fatigue life of the riveted plate with rivet material of 2117-T4 under the same process conditions is increased by 0.12-0.44 times.
automatic rivetingfinite element analysisresidual stressfatigue performance
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