Dynamic instability of variable stiffness composite plates

Loja, M. A. R.; Barbosa, J. Infante; Soares, Cristóvão M. Mota

doi:10.1016/j.compstruct.2017.09.046

Cited by 43 publications

(13 citation statements)

References 24 publications

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“…In [14,15], based on the Bolotin method, the problem of dynamic instability of composite plates of variable thickness is solved. The influence of the geometrical and physical-mechanical parameters of the plate on the dynamic instability region is shown.…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of an orthotropic viscoelastic cylindrical panel of variable thickness

et al. 2021

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The intensive development of the modern industry is associated with the emergence of a variety of new composite materials. Plates, panels, and shells of variable thickness made of such materials are widely used in engineering and machine building. Modern technology for the manufacture of thin-walled structures of any configuration makes it possible to obtain structures with a given thickness variation law. Such thin-walled structures are subjected to various loads, including periodic ones. Nonlinear parametric vibrations of an orthotropic viscoelastic cylindrical panel of variable thickness are investigated without considering the elastic wave propagation. To derive a mathematical model of the problem, the Kirchhoff-Love theory is used in a geometrically nonlinear setting. The viscoelastic properties of a cylindrical panel are described by the hereditary Boltzmann-Volterra theory with a three-parameter Koltunov-Rzhanitsyn relaxation kernel. The problem is solved by the Bubnov-Galerkin method in combination with the numerical method. For the numerical implementation of the problem, an algorithm and a computer program were developed in the Delphi algorithmic language. Nonlinear parametric vibrations of orthotropic viscoelastic cylindrical panels under external periodic load were investigated. The influence of various physical, mechanical, and geometric parameters on the panel behavior, such as the thickness, viscoelastic and inhomogeneous properties of the material, external periodic load, were studied.

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Section: Introductionmentioning

confidence: 99%

Dynamic analysis of an orthotropic viscoelastic cylindrical panel of variable thickness

et al. 2021

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“…Tan and Nie have carried out the free and forced vibrations of variable thickness composite annular thin plates with elastically restrained edges employing the method of weighted residuals. Loja et al have analyzed the dynamic instability of VSCL subjected to periodic inplane load using the Rayleigh‐Ritz method.…”

Section: Introductionmentioning

confidence: 99%

Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

et al. 2018

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In this article, the thermoelastic stability behavior of curvilinear fiber‐reinforced composite laminates is investigated using a shear flexible plate theory. The laminate is composed of layers that make use of curvilinear fibers to create spatial variation of stiffness due to the continuous change of fiber orientation within the lamina. Such composite laminates, subjected to different thermal loads like uniform and non‐uniform temperature distributions, are considered in this analysis. The governing equations obtained using the principle of minimization of total potential energy, are solved for evaluating the critical buckling temperature. The displacement fields of pre‐buckling of the laminate are evaluated before proceeding for the thermal buckling analysis. The formulation is checked against available solutions in the literature. A detailed parametric study considering important design parameters such as curvilinear fiber angles, lay‐up, thickness ratio, coefficients of thermal expansion, and modular ratio on the thermoelastic stability/buckling behavior of composite laminates is made. The present analysis highlights the substantial change in the critical buckling loads due to the curvilinear fiber angles, lay‐up and boundary conditions. The new results presented here for curvilinear fiber‐reinforced composite laminate with clamped/mixed boundary conditions may be useful in assessing similar studies based on higher‐order theories or other numerical studies. POLYM. COMPOS., 40:2876–2890, 2019. © 2018 Society of Plastics Engineers

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“…Guenanou and Houmat [21] developed a curved hierarchical square finite element for the free vibration analysis of symmetrically laminated composite circular plates with curvilinear fibers based on the first-order shear deformation theory. Loja et al [22] investigated the dynamic instability response of variable stiffness composite plates using the methods of Bolotin and Rayleigh. Houmat [23] developed a brick p-element for the free vibration analysis of variable stiffness laminated composite rectangular plates with curvilinear fibers based on three-dimensional elasticity theory.…”

Section: Introductionmentioning

confidence: 99%

“…Loja et al. [22] investigated the dynamic instability response of variable stiffness composite plates using the methods of Bolotin and Rayleigh. Houmat [23] developed a brick p -element for the free vibration analysis of variable stiffness laminated composite rectangular plates with curvilinear fibers based on three-dimensional elasticity theory.…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional solutions for free vibration of variable stiffness laminated sandwich plates with curvilinear fibers

Houmat

2018

Jnl of Sandwich Structures & Materials

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This paper is concerned with the free vibration of variable stiffness laminated sandwich plates with curvilinear fibers. The three-dimensional elasticity theory and the p-version of the finite element method are adopted for the analysis. The skin is composed of one or more plies with curvilinear fibers. The fiber path orientation angle in a ply is assumed to vary linearly with the x coordinate. The plies may be stacked symmetrically or anti-symmetrically with respect to the middle surface of the plate. Each layer is modeled as one brick p-element. The principle of virtual displacements is used to derive the element stiffness and mass matrices. The generalized displacements at vertices, edges, and faces shared by elements are matched to ensure inter-element compatibility. Since no solutions are available for the free vibration of such variable stiffness laminated sandwich plates, the validity, convergence, and accuracy of the present three-dimensional method are established by comparing with existing three-dimensional frequencies for constant stiffness laminated sandwich plates with rectilinear fibers. The study reveals that inter-layer modal bending stresses are discontinuous; modal transverse shearing stresses are constant in the core; the sign of modal transverse shearing stresses can change through the thickness of the skin; and the shape of modal cross-sectional warping is influenced by the mode number and stacking sequence of plies. Three-dimensional frequencies are presented for different fiber orientation angles, boundary conditions, aspect ratios, thickness ratios, core/skin thickness ratios, and stacking sequences of plies. The accurate results presented here will serve as a benchmark for future investigations.

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Dynamic instability of variable stiffness composite plates

Cited by 43 publications

References 24 publications

Dynamic analysis of an orthotropic viscoelastic cylindrical panel of variable thickness

Dynamic analysis of an orthotropic viscoelastic cylindrical panel of variable thickness

Thermoelastic Stability Behavior of Curvilinear Fiber‐Reinforced Composite Laminates With Different Boundary Conditions

Three-dimensional solutions for free vibration of variable stiffness laminated sandwich plates with curvilinear fibers

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