Effects of ply orientation on nonlinear buckling of Aircraft composite stiffened panel
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 emphasi...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Gruppo Italiano Frattura
2019-10-01
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| Series: | Fracture and Structural Integrity |
| Subjects: | |
| Online Access: | https://www.fracturae.com/index.php/fis/article/view/2548/2697 |
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| Summary: | 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) |
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| ISSN: | 1971-8993 |