Abstract: In this study, gradual demand for curved, stiffened panels composite emerged from Carbon Fiber Reinforced Plastics (CFRP) these are structures that are frequently used in aerospace engineering. Up to 50% of the primary structure of the Boeing 787 is made up of woven graphite-epoxy. This research emphasizes the buckling analysis of stiffened composite panels using the nonlinear, finite element modeling. The stiffened panel is assumed to be subjected to a uniform axial compression load of 10 kN. For the nonlinear buckling analysis, a stiffened composite panel is made of Carbon Fibre Composite (CFC) in epoxy, Kevlar in epoxy and E-Glass (EG) in epoxy. Due to the fact that there are numerous stiffened composite panels materials this study, therefore uses a numerical approach to present the study and results of the nonlinear static buckling analysis of i-stiffened on different composite panels. This research also presented the effect of the different ply orientations using Abaqus Finite Element Analysis (FEA).
Ouadia Mouhat, Abdellatif Khamlichi, Hasnae Boubel, Oumnia Elmrabet, Mohamed Rougui and Ahmed El Bouhmidi, 2020. Effects of Ply Orientation on Nonlinear Buckling of Aircraft Stiffened Composite Panel. Research Journal of Applied Sciences, 15: 139-149.