TY  - JOUR
T1  - Effects of Ply Orientation on Nonlinear Buckling of Aircraft Stiffened Composite Panel
AU - Mouhat, Ouadia AU - Khamlichi, Abdellatif AU - Boubel, Hasnae AU - Elmrabet, Oumnia AU - Rougui, Mohamed AU - El Bouhmidi, Ahmed 
JO  - Research Journal of Applied Sciences
VL  - 15
IS  - 4
SP  - 139
EP  - 149
PY  - 2020
DA  - 2001/08/19
SN  - 1815-932x
DO  - rjasci.2020.139.149
UR  - https://makhillpublications.co/view-article.php?doi=rjasci.2020.139.149
KW  - Stiffened composite panels
KW  -nonlinear buckling analysis
KW  -ply orientations
KW  -FEM
KW  -CFC
KW  -FEA
AB  - 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).
ER  -