An efficient computer program for the large deflection analysis of rectangular orthotropic plates

Little, G.H.

doi:10.1016/0045-7949(87)90277-x

Cited by 13 publications

(2 citation statements)

References 4 publications

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“…For plates, Yamaki [16] and Little [17] have performed post-buckling analysis of rectangular plates with small initial curvature. Modelling of initial imperfection by the ÿnite-element method has also been described, for instance Kapania and Yang [18] and Saigal et al [19].…”

Section: Introductionmentioning

confidence: 99%

Post‐buckling analysis of imperfect laminates using finite strips based on a higher‐order plate theory

Zou¹,

Lam²

2003

Numerical Meth Engineering

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SUMMARYA ÿnite strip procedure has been developed for the post-buckling analysis of composite laminates when subjected to progressive end shortening. The ÿnite strips are developed based on a higher-order shear deformation plate theory and there are nine variables at each nodal line. Initial imperfection expressed in the form of suitable trigonometric function is allowed. Examples including isotropic plates and laminates with arbitrary lay-up arrangement are presented. Numerical results for laminates with and without initial imperfection are used to illustrate the e ect of imperfection.

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Section: Introductionmentioning

confidence: 99%

Post‐buckling analysis of imperfect laminates using finite strips based on a higher‐order plate theory

Zou¹,

Lam²

2003

Numerical Meth Engineering

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“…Some formulations consider the panel, without the stiffeners, subjected to simply-supported or clamped conditions (8)(9)(10)(11) . Analytical approaches are found also for panels subjected to elastically restrained boundary conditions, where the elasticity of the boundary conditions accounts for the effect of the stiffener (12)(13)(14) .…”

Section: Introductionmentioning

confidence: 99%

A fast procedure for the design of composite stiffened panels

Bisagni

Vescovini

2015

Aeronaut.j.

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This paper describes the analysis and the minimum weight optimisation of a fuselage composite stiffened panel made from carbon/epoxy material and stiffened by five omega stringers. The panel investigated inside the European project MAAXIMUS is studied using a fast tool, which relies on a semi-analytical procedure for the analysis and on genetic algorithms for the optimisation. The semi-analytical approach is used to compute the buckling load and to study the post-buckling response. Different design variables are considered during the optimisation, such as the stacking sequences of the skin and the stiffener, the geometry and the cross-section of the stiffener. The comparison between finite element and fast tool results reveals the ability of the formulation to predict the buckling load and the post-buckling response of the panel. The reduced CPU time necessary for the analysis and the optimisation makes the procedure an attractive strategy to improve the effectiveness of the preliminary design phases.

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Post-buckling analysis of a strut with general initial imperfection

Lam

1998

Int. J. Numer. Meth. Engng.

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Computational procedure has been presented for the post-buckling analysis of a strut with initial imperfection when subjected to progressive end shortening. Polynomial expression in very general form is used to simulate the actual initial imperfection, while the deformations are expressed by suitable trigonometric series. Geometric non-linearity is introduced into the strain-displacement relations in a manner that is consistent with the von Karman assumptions. Non-linear equilibrium equations are solved by a NewtonRaphson procedure. Results are presented for cases with symmetric and non-symmetric initial imperfection. Good comparison with other solutions and experimental results is obtained in all applications.

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An efficient computer program for the large deflection analysis of rectangular orthotropic plates

Cited by 13 publications

References 4 publications

Post‐buckling analysis of imperfect laminates using finite strips based on a higher‐order plate theory

Post‐buckling analysis of imperfect laminates using finite strips based on a higher‐order plate theory

A fast procedure for the design of composite stiffened panels

Post-buckling analysis of a strut with general initial imperfection

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