Buckling, postbuckling, and crippling of shallow-curved composite plates with edge stiffeners

Arnold, Rocky R.; Yoo, Seung Yup; Mayers, J.

doi:10.2514/3.45348

Cited by 7 publications

(4 citation statements)

References 13 publications

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“…Even though the curvature can significantly increase the buckling load of a plate, it mostly does not influence the postbuckling failure load. For shallow curved isotropic and orthotropic plates results obtained by [8][9][10] show that the postbuckling stiffness rapidly decreases to the stiffness of a flat plate after buckling. The effect of curvature is therefore neglected in the present study.…”

Section: Buckling Load Calculationmentioning

confidence: 95%

“…Most of the papers initially referred to in the buckling load calculation section handle the behaviour after buckling as well as the buckling load calculation itself (e.g. [8][9][10][11][12][13][14][15][16][17][18][19][20][21][22], [24]). The present study follows the analysis scheme as proposed by [22] for isotropic simply supported plates.…”

Section: Postbuckling Behaviourmentioning

confidence: 99%

“…[8][9][10][11][12][13][14][15][16][17][18]) when loaded in pure compression for isotropic, orthotropic or even anisotropic material behaviour and different boundary conditions. Other authors ( [19][20][21]) have analysed the behaviour of a plate loaded in pure shear with clamped or simply supported boundary conditions.…”

Section: Buckling Load Calculationmentioning

confidence: 99%

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Preliminary design of composite fuselage structures using analytical rapid sizing methods

Quatmann

Reimerdes

2011

CEAS Aeronaut J

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The increasing use of composite materials in aircraft structures aims in reducing the structural weight significantly. In order to exploit the advantages of composite materials especially within a large-scale optimization calculation, a model for a computationally efficient structural analysis needs to be developed. In this regard, algorithms need to be developed to rapidly compute stress distribution and critical loads for both strength and stability of the composite aircraft fuselage. Therefore, sizing methods for metallic and composite orthotropically stiffened fuselage structures have been reviewed. For critical load computation, fibre fracture and inter-fibre fracture need to be taken into consideration with respect to strength. Regarding stability, the critical buckling loads of skins and stringers as well as the critical crippling load need to be taken into account. The buckling of stringers often occurs after the skin buckling load is exceeded. Hence, the postbuckling behaviour needs to be analyzed and load redistributions in the postbuckling range have to be taken into consideration. These load redistributions can generally be calculated numerically using either the finite element method or the finite strip method (Möcker and Reimerdes in Compos Struct 73:237-243, 2006) as well as analytically. In order to minimize the computational time, the postbuckling behaviour of the skins regarded as composite plates is computed analytically within this work by means of a computation of effective stiffnesses for global analysis and local failure load computation. Even though the postbuckling behaviour of metallic and composite plates has been widely studied in literature, only few work has been spent on the analytical or semi-analytical derivation of methods for the common load case of combined compression and shear loading. As the preliminary design of an aircraft fuselage requires a rapid and sufficiently accurate description of the postbuckling behaviour, the postbuckling behaviour of an orthotropic composite plate under combined compression and shear loading is analytically analyzed within the present work. The derived rapid sizing method for postbuckling significantly reduces the computational time when compared to the computational time needed for a nonlinear finite element computation. In this regard, it even allows for the consideration of postbuckling behaviour within a large-scale optimization computation of complete fuselage structures.

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Section: Buckling Load Calculationmentioning

confidence: 95%

Section: Postbuckling Behaviourmentioning

confidence: 99%

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Preliminary design of composite fuselage structures using analytical rapid sizing methods

Quatmann

Reimerdes

2011

CEAS Aeronaut J

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“…The panel was going through axial compression in that study. The crippling and post-buckling of shallow curve laminates are studied by Arnold et al (1986). In this study only the edges of the plates were stiffened.…”

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confidence: 99%

A Review on the Effect of Delamination on the Performance of Composite Plate

Imran¹,

Khan²,

Badshah³

2018

Pak. j. sci. ind. res. Ser. A: phys. sci.

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Buckling and postbuckling analyses of laminated anisotropic structures

Noor

Peters

1989

Numerical Meth Engineering

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A review is given of recent advances in two aspects of the numerical simulation of the buckling and postbuckling responses of composite structures. The first aspect is exploiting non-traditional symmetries exhibited by composite structures: and strategies for reducing the size of the model and the cost of the buckling and postbuckling analyses in the presence of symmetry-breaking conditions (e.g. asymmetry of the material. geometry, and/or loading). The second aspect pertains to the prediction of onset of local delamination in the postbuckling range and accurate determination of transverse shear stresses in the structure. The accuracy and effectiveness of the strategies developed are demonstrated by means of a numerical example.

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Buckling, postbuckling, and crippling of shallow-curved composite plates with edge stiffeners

Cited by 7 publications

References 13 publications

Preliminary design of composite fuselage structures using analytical rapid sizing methods

Preliminary design of composite fuselage structures using analytical rapid sizing methods

A Review on the Effect of Delamination on the Performance of Composite Plate

Buckling and postbuckling analyses of laminated anisotropic structures

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