Abstract
In this paper, 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 . 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 paper, 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).
Highlights
The fuselage is the main part of the aircraft, which is made up of so many stiffened composite panels; the reinforced structures are made by arranging the members and frames in vertical, horizontal, diagonal and longitudinal directions
European Commission POSICOSS (EC), which continued from January 2000 to September 2004, is the project of regular quadrennial COCOMAT, which extended until September 2008, contributed to this goal [1,2,3]
When the structure is subjected to axial compression loading, due to the design method, a short deformation will be created on the structure precisely when the load is at a critical level
Summary
The fuselage is the main part of the aircraft, which is made up of so many stiffened composite panels; the reinforced structures are made by arranging the members and frames in vertical, horizontal, diagonal and longitudinal directions. In this complementary study, we presented a formulation adapted for the stability analysis of the composite stiffened panel. Where x et y the average rotations of a perpendicular line, within each element are can be expressed in terms of the unknown number of nodes using the following functions Ni form: N u Ni ui , v Nivi , w Ni wi i 1 i 1 i 1. Where C is the material constant matrix, the paper presents the evaluation of stresses and strains, deformations for static buckling analysis 19
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