The Experts below are selected from a list of 255 Experts worldwide ranked by ideXlab platform
Z G Azizian - One of the best experts on this subject based on the ideXlab platform.
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non linear finite strip analysis of rectangular laminates under end shortening using Classical Plate Theory
International Journal for Numerical Methods in Engineering, 1992Co-Authors: D J Dawe, Z G AzizianAbstract:The finite strip method is developed for predicting the geometrically non-linear response of rectangular composite laminates with simply supported ends when subjected to uniform end shortening in their plane. At the loaded ends lateral in-plane expansion may be allowed freely or may be prevented completely in different versions of the approach. The permitted laminate material properties are quite general, encompassing anisotropy and full coupling between in-plane and out-of-plane behaviour. The analysis is based on the use of the Classical Plate Theory and the non-linearity is introduced in the strain-displacement equations in the manner of the von Karman assumptions. Three different types of finite strip are presented with either linear, quadratic or cubic interpolation of the membrane displacement components across a strip: in each case the bending displacement component varies cubically across a strip. Results are presented for isotropic Plates and for unsymmetric cross-ply, angle-ply and arbitrary laminates.
Kuangchong Wu - One of the best experts on this subject based on the ideXlab platform.
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stress intensity factors and energy release rate for anisotropic Plates based on the Classical Plate Theory
Composites Part B-engineering, 2016Co-Authors: Kuangchong WuAbstract:Abstract The stress and displacement fields near the tip of a through crack in an anisotropic elastic Plate are examined according to the Classical Plate Theory. The Plate is assumed to be subjected to bending moments, twisting moments, or transverse shear forces. In particular, the stresses at the prolongation of the crack and the relative crack face displacements are derived. The results are used to define stress intensity factors which are consistent with those for isotropic material in Ref. [6]. An explicit expression for the energy release rate in terms of the stress intensity factors is obtained using the path-independent J-integral. Analytic solutions are given for the stress intensity factors of a crack in an infinite Plate under uniform bending moments, twisting moments, or transverse shear forces. It is shown that the stress intensity factors are zero and the stresses at the crack tip are finite if only twisting moments are applied. A universal relationship between the Classical Theory stress intensity factors and the Reissner Theory stress intensity factors for thin orthotropic Plates under symmetric bending is also derived.
F W Williams - One of the best experts on this subject based on the ideXlab platform.
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buckling analysis of skew Plate assemblies Classical Plate Theory results incorporating lagrangian multipliers
Computers & Structures, 1995Co-Authors: C B York, F W WilliamsAbstract:A procedure is presented for the buckling analysis of prismatic skew Plate assemblies subject to invariant in-plane stresses. Based on the exact solution of the Plate differential equations, the method of Lagrangian multipliers is used to enforce the transverse skew boundaries by a sufficient number of point constraints. Analysis assumes that the Plate is infinitely long and that supports repeat at bay length intervals, typifying the continuity found in aircraft wing construction. Following a brief derivation of the formulation adopted, results are presented and comparisons are made with other analyses for an unstiffened isotropic skew Plate, subject to pure compression loading with both simply supported and clamped boundary conditions. Results for four benchmark stiffened panels, i.e. Plate assemblies, incorporating composite material and combined loading are also given for a range of skew angles.
D J Dawe - One of the best experts on this subject based on the ideXlab platform.
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non linear finite strip analysis of rectangular laminates under end shortening using Classical Plate Theory
International Journal for Numerical Methods in Engineering, 1992Co-Authors: D J Dawe, Z G AzizianAbstract:The finite strip method is developed for predicting the geometrically non-linear response of rectangular composite laminates with simply supported ends when subjected to uniform end shortening in their plane. At the loaded ends lateral in-plane expansion may be allowed freely or may be prevented completely in different versions of the approach. The permitted laminate material properties are quite general, encompassing anisotropy and full coupling between in-plane and out-of-plane behaviour. The analysis is based on the use of the Classical Plate Theory and the non-linearity is introduced in the strain-displacement equations in the manner of the von Karman assumptions. Three different types of finite strip are presented with either linear, quadratic or cubic interpolation of the membrane displacement components across a strip: in each case the bending displacement component varies cubically across a strip. Results are presented for isotropic Plates and for unsymmetric cross-ply, angle-ply and arbitrary laminates.
C B York - One of the best experts on this subject based on the ideXlab platform.
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buckling analysis of skew Plate assemblies Classical Plate Theory results incorporating lagrangian multipliers
Computers & Structures, 1995Co-Authors: C B York, F W WilliamsAbstract:A procedure is presented for the buckling analysis of prismatic skew Plate assemblies subject to invariant in-plane stresses. Based on the exact solution of the Plate differential equations, the method of Lagrangian multipliers is used to enforce the transverse skew boundaries by a sufficient number of point constraints. Analysis assumes that the Plate is infinitely long and that supports repeat at bay length intervals, typifying the continuity found in aircraft wing construction. Following a brief derivation of the formulation adopted, results are presented and comparisons are made with other analyses for an unstiffened isotropic skew Plate, subject to pure compression loading with both simply supported and clamped boundary conditions. Results for four benchmark stiffened panels, i.e. Plate assemblies, incorporating composite material and combined loading are also given for a range of skew angles.