Effects of ply orientation on nonlinear buckling of Aircraft composite stiffened panel

• Main Authors: Ouadia Mouhat, Abdelmajid Bybi, Ahmed El Bouhmidi, Mohamed Rougui
• Format: Article
• Language: English
• Published: Gruppo Italiano Frattura 2019-10-01
• Series: Frattura ed Integrità Strutturale
• Subjects: stiffened composite panels; nonlinear buckling analysis; fem ply orientations
• Online Access: https://www.fracturae.com/index.php/fis/article/view/2548/2697

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. 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)