Issue 50

O. Mouhat et alii, Frattura ed Integrità Strutturale, 50 (2019) 126-140; DOI: 10.3221/IGF-ESIS.50.12 126 Effects of ply orientation on nonlinear buckling of Aircraft composite stiffened panel Ouadia Mouhat Mohammed V University, Structure LGCE, EST Sale -CED of Mohammadia Engineering School, Rabat, Morocco. Ouadie.mouhat@gmail.com Abdelmajid Bybi Mohammed V University in Rabat, EST Sale - Morocco MEAT - Materials Energy Acoustics Team-CED of Mohammadia Engineering School, Rabat. Ahmed El Bouhmidi, Mohamed Rougui Mohammed V University, Structure LGCE, EST Sale -CED of Mohammadia Engineering School, Rabat, Morocco. A BSTRACT . In this paper the demand for curved stiffened panels composite from carbon fiber reinforced plastics (CFRP) has emerged; these structures are most frequently used in aerospace engineering. Nearly 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 modelling. 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 many 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 various composite panels. This research also presented the effect of the different ply orientations using Abaqus finite element analysis (FEA). K EYWORDS . Stiffened composite panels; Nonlinear buckling analysis; FEM ply orientations. Citation: Mouhat, O, Bybi, A., El Bouhmidi, A., Rougui, M., Effects of ply orientation on nonlinear buckling of aircraft composite stiffened panel, Frattura ed Integrità Strutturale, 50 (2019) 126-140. Received: 22.06.2019 Accepted: 29.07.2019 Published: 01.10.2019 Copyright: © 2019 This is an open access article under the terms of the CC-BY 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited. I NTRODUCTION he 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. The study of fuselage sections is still very costly. This research is mainly focused on reinforced panels, considering the fact that there are two categories of the panel; considering the limit state, it is important more investigation was carried on this subject, so as to uncover greater findings, which is usually the T