Effect of skin parameters on the buckling and post-buckling behavior of composite stiffened panels under axial load

doi:10.19936/j.cnki.2096-8000.20230428.015

Abstract

Abstract: There are a large number of stiffened panels in the aircraft, and the use of composite materials to replace traditional metal materials to make stiffened panels can reduce weight and improve performance. In order to study the effect of different skin parameters on the buckling and post-buckling behavior of composite stiffened panels under axial compression loads, a finite element model was established based on ABAQUS. First, the eigenvalue method is used for buckling analysis, then the ABAQUS dynamic explicit is used for quasi-static simulation analysis (post-buckling analysis), and finally the axial compression test is performed. The results show that the finite element analysis results are roughly consistent with the experimental values, that is, the model solution method can correctly forecast the post-buckling load. The difference of the skin parameters changes the buckling mode of the stiffened panels, and has a significant impact on the post-buckling behavior, which significantly changes the load-bearing capacity of the stiffener structure. The research results are of great significance for optimizing the bearing capacity of composite stiffened panels and improving the efficiency of aircraft structure design.

Key words: composite stiffened panel, finite element, quasi-static analysis, buckling, post-buckling

CLC Number:

TB332

XU Liang, BIAN Yubo, SONG Wanwan, ZHOU Song, XING Bendong. Effect of skin parameters on the buckling and post-buckling behavior of composite stiffened panels under axial load[J]. COMPOSITES SCIENCE AND ENGINEERING, 2023, 0(4): 100-106.

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