Experimental and numerical research on the calculation methods for buckling and post-buckling of aircraft tail inclined stiffened panel under compression load

The purpose of this paper is to investigate the buckling and post-buckling behavior of inclined stiffened composite panels under axial compression load. Two types of stiffened composite panels with two inclined stringers and one longitudinal stringer were manufactured and tested, and the buckling load, ultimate load and other required Structural properties of the inclined stiffened composite panels were obtained. The test results show that the failure load of two type panels are 3.19 times and 7.79 times of buckling load, respectively, indicating that such inclined stiffened panels have a large post-buckling capacity. The combination of Hashin failure criterion and Cohesive model was used to conduct finite element modeling, which accurately predicts the buckling, post-buckling and damage modes of the panel. Based on the classical lamination theory, stiffness calculation method of inclined stringer was proposed. The linear relationship between the stiffness of inclined stringer and buckling load was verified. The engineering calculation methods for buckling load and failure load have been established to improve calculation efficiency. The research in this paper can provide reference for aircraft Structural design.