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

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

doi:10.3221/igf-esis.50.12

Cited by 5 publications

(3 citation statements)

References 18 publications

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“…As far as buckling characteristics of laminated fiber-reinforced composite materials are concerned, most of the available literature data refer to plates with and without cutouts. 15,16 The buckling behavior of rectangular, 17 circular, 18 elliptical, 19 and skew 20 plates with different end conditions, [21][22][23] loadings, 24 number of layers, 25,26 ply orientations, 27,28 stacking sequences, 29,30 aspect ratios, 31 thicknesses, 32 cutout shapes 33,34 and material nonlinearity 35 have been studied by many researchers. However, some techniques that can increase the buckling performance of fiber-reinforced composite materials are also widely preferred.…”

Section: Introductionmentioning

confidence: 99%

Buckling characteristics of nano‐silica doped carbon fiber reinforced composites having cutouts

Özdemir,

Özbek,

Bozkurt

et al. 2024

Polymer Composites

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The current study presents an experimental investigation devoted to the nano‐silica and cutout effects on the axial and lateral buckling responses of carbon/epoxy fiber‐reinforced composite laminates. To this end, specimens manufactured by vacuum bagging after hand layup technique were prepared at various amounts of nano‐silica (0.5%, 1.0%, 1.5%, 2.0%, and 3.0% by weight) incorporated into epoxy resin. Furthermore, semi‐circular and circular cutouts were opened on specimens to understand cutout effect on buckling characteristics of specimens. The results demonstrated that nano‐silica had a significant effect on buckling behaviors of the carbon fiber‐reinforced composites. Regardless of cutout presences, maximum critical axial (393.33 N, 361.67 N, 320 N for W, C and S) and lateral buckling loads (34.67 N, 33 N, 32.33 N for W, C and S), were achieved from the samples having 1.5 wt. % nano‐silica. In specimens having no cutout, maximum improvements of 72.26% in axial and 48.6% in lateral directions were achieved from the specimens having 1.5 wt. % nano‐silica content. A further amount of nano‐silica addition decreased the resistance to buckling of the specimens. Also, the presence of cutouts on the specimens led to decreases in critical loads. The decreases of 1.5 wt. % nano‐silica doped specimens without cutout in the axial and lateral critical buckling loads, respectively, were seen as 22.9% and 7.24% for circular cutout, 8.75% and 5.06% for semi‐circular cutout. It was concluded that cutout processing and nano‐silica additions should be taken into consideration in a material that may be exposed the buckling failures.Highlights Nano‐silica impact on buckling behaviors of carbon fiber‐reinforced composites Cutout effects on buckling properties of carbon fiber‐reinforced composites Failure modes of carbon fiber‐reinforced composites with nano‐silica particles Findings showed that 1.5 wt. % nano‐silica inclusion exhibited the best values for buckling.

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Section: Introductionmentioning

confidence: 99%

Buckling characteristics of nano‐silica doped carbon fiber reinforced composites having cutouts

Özdemir,

Özbek,

Bozkurt

et al. 2024

Polymer Composites

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“…15 Poorveis et al 16 developed a new sub-parametric spline finite strip method (SSFSM) to analyze axially loaded composite cylindrical panel having cutout. Mouhat et al 17 used ABAQUS software for non-linear buckling analysis of stiffened composite panels having various ply orientations. Mohammed et al 18 considered the buckling of thin cylindrical composite panel with oval cutout using ABAQUS software.…”

Section: Introductionmentioning

confidence: 99%

Buckling behavior of laminated composite stiffened cylindrical shell panels having cutout for different parametric variations

Sahoo¹

2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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Buckling of composite stiffened cylindrical shell panels having cutout is analyzed using the finite element approach. Shell panel and stiffeners are modeled using first-order shear deformation theory and considering displacement compatibility at the stiffener-panel interface. Convergence and validation studies are conducted to establish the accuracy of the present approach. An attempt is made to maximize the uniaxial and biaxial buckling loads by varying the lamination, boundary conditions, load position, depth of stiffeners, and their arrangements. Parametric studies show that buckling load and mode shapes depend on the size of cutout, ratio of shell width to thickness, degree of orthotropy, and fiber orientation angle. The parametric variations considered here may help the practicing engineers to have an elaborate design aid for improving the buckling strength of such shell panels.

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“…Poorveis et al 48 used sub-parametric strip element method for analysis of composite cylindrical panel with cut-out. Mouhat et al 49 used nonlinear finite element modeling to consider the effect of ply orientation on nonlinear buckling of composite stiffened panel. Shojaee et al 50 investigated stiffener effect on buckling strength of composite laminates with circular cutout.…”

Section: Introductionmentioning

confidence: 99%

Buckling characteristics of cut-out borne composite stiffened hyperbolic paraboloid shell panel

Sahoo¹

2021

Proceedings of the Institution of Mechanical Engineers, Part L:

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The present study investigates buckling characteristics of cut-out borne stiffened hyperbolic paraboloid shell panel made of laminated composites using finite element analysis to evaluate the governing differential equations of global buckling of the structure. The finite element code is validated by solving benchmark problems from literature. Different parametric variations are studied to find the optimum panel buckling load. Laminations, boundary conditions, depth of stiffener and arrangement of stiffeners are found to influence the panel buckling load. Effect of different parameters like cut-out size, shell width to thickness ratio, degree of orthotropy and fiber orientation angle of the composite layers on buckling load are also studied. Parametric and comparative studies are conducted to analyze the buckling strength of composite hyperbolic paraboloid shell panel with cut-out.

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

Cited by 5 publications

References 18 publications

Buckling characteristics of nano‐silica doped carbon fiber reinforced composites having cutouts

Buckling characteristics of nano‐silica doped carbon fiber reinforced composites having cutouts

Buckling behavior of laminated composite stiffened cylindrical shell panels having cutout for different parametric variations

Buckling characteristics of cut-out borne composite stiffened hyperbolic paraboloid shell panel

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