@article{MAKHILLRJAS202015410239,
    title = {Effects of Ply Orientation on Nonlinear Buckling of Aircraft Stiffened Composite Panel},
    journal = {Research Journal of Applied Sciences},
    volume = {15},
    number = {4},
    pages = {139-149},
    year = {2020},
    issn = {1815-932x},
    doi = {rjasci.2020.139.149},
    url = {https://makhillpublications.co/view-article.php?issn=1815-932x&doi=rjasci.2020.139.149},
    author = {Ouadia,Abdellatif,Hasnae,Oumnia,Mohamed and},
    keywords = {Stiffened composite panels,nonlinear buckling analysis,ply orientations,FEM,CFC,FEA},
    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).}
    }