Ouadia  Mouhat, Abdellatif  Khamlichi, Hasnae  Boubel, Oumnia  Elmrabet, Mohamed  Rougui, Ahmed  El Bouhmidi, 
    Effects of Ply Orientation on Nonlinear Buckling of Aircraft Stiffened Composite Panel,
    Research Journal of Applied Sciences,
    Volume 15,Issue 4,
    2020,
    Pages 139-149,
    ISSN 1815-932x,
    rjasci.2020.139.149,
    (https://makhillpublications.co/view-article.php?doi=rjasci.2020.139.149)
    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).
    Keywords: Stiffened composite panels;nonlinear buckling analysis;ply orientations;FEM;CFC;FEA