The Effects of Ply Orientation on Nonlinear Buckling of Aircraft composite Stiffened Panel

Ouadia Mouhat; Abdelmajid Bybi; Ahmed El Bouhmidi; Mohamed Rougui

doi:10.3221/IGF-ESIS.50.12

The Effects of Ply Orientation on Nonlinear Buckling of Aircraft composite Stiffened Panel

Authors

Ouadia Mouhat Mohammed V University, Structure LGCE l’EST, Salé -CED de l’EMI, Rabat, Morocco
Abdelmajid Bybi Mohammed V University in Rabat, EST Sale - Morocco MEAT - Materials Energy Acoustics Team-CED of Mohammadia Engineering School, Rabat.
Ahmed El Bouhmidi Mohammed V University, Structure LGCE, EST Sale -CED of Mohammadia Engineering School, Rabat, Morocco.
Mohamed Rougui Mohammed V University, Structure LGCE, EST Sale -CED of Mohammadia Engineering School, Rabat, Morocco.

DOI:

https://doi.org/10.3221/IGF-ESIS.50.12

Keywords:

Stiffened composite panels, Nonlinear buckling analysis, FEM ply orientations

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).

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Published

10-08-2019

Issue

Vol. 13 No. 50 (2019): October 2019

Section

Advanced Manufacturing and Processing

License

Copyright
Authors are allowed to retain both the copyright and the publishing rights of their articles without restrictions.

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How to Cite

The Effects of Ply Orientation on Nonlinear Buckling of Aircraft composite Stiffened Panel. (2019). Frattura Ed Integrità Strutturale, 13(50), 126-140. https://doi.org/10.3221/IGF-ESIS.50.12