Improved Efficient Zigzag and Third Order Theories for Circular Cylindrical Shells Under Thermal Loading

Thermal deformations in cross-ply laminated shells are investigated. The state space approach is used to generate exact solutions for the thermoelastic response of crossply spherical, cylindrical and doubly curved shells for various boundary conditions and subjected to general temperature field. The shells possess two parallel edges simply supported and the remaining ones having any possible combination of boundary conditions: free, clamped or simply supported. A rigorous thick deep first order shear deformation shell theory is used in the analysis. Deflections are computed for shells with various boundary conditions undergoing uniform and linearly varying temperature through the thickness. The exact solutions for thermal deflections can be used as benchmarks for approximate solutions such as Rayleigh-Ritz and finite element methods.

Section: Thermoelastic Response Of Cross-ply Laminated Shellsmentioning

confidence: 99%

Thermoelastic Response of Cross-Ply Laminated Shells Based on a Rigorous Shell Theory

Khdeir

2012

“…They solved the static problem of a cylindrical shell subjected to a temperature field and inner pressure loading. Dumir et al [12] provided two-and three-dimensional exact solutions for simply supported cross-ply laminated shell panels using the HSDT and zigzag theory.…”

Section: Introductionmentioning

confidence: 99%

“…In design of laminated shell panels, especially for aerospace vehicles such as high-speed aircrafts, rockets, and spacecrafts, which are subjected to thermal loads due to aerodynamic and/or solar radiation heating, thermal loading effects, must be considered. The thermo-elastic behavior of composite shells has been previously considered in the literature [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Thermal Bending Analysis of Doubly Curved Composite Laminated Shell Panels with General Boundary Conditions and Laminations

Maghami

Tahani

2015

Thermal bending analysis of doubly curved laminated shell panels with general boundary conditions and laminations is presented. The equations of equilibrium are derived in the form of two coupled sets of ordinary differential equations based on a general shell theory and solved through the state-space approach in a repeated manner. It is depicted that the results of the present method are in great agreement with analytical solutions. Cylindrical shell panels with general boundary conditions and laminations, where no analytical solution is available, are solved. It is found that the present method exhibits a high convergence rate as well as presenting accurate results in all cases.

“…A simple, semianalytical model for simply supported composite and sandwich plates subjected to thermal load has been presented in [9]. An improved zigzag and third-order theories are presented in [10] for laminated circular cylindrical shells and shell panels under thermal loading. The theories are assessed in comparison with exact 3D thermoelasticity solution for simply supported shells and shell panels for different lay-ups.…”

Section: Introductionmentioning

confidence: 99%

An Exact Solution for the Thermoelastic Deformations of Cross-Ply Laminated Arches with Arbitrary Boundary Conditions

Khdeir

2011

Thermal deformations in symmetric and antisymmetric cross-ply laminated arches are investigated. The state-space approach has been used to generate exact solutions for the thermoelastic response of cross-ply arches for arbitrary boundary conditions and subjected to general temperature field. A rigorous first-order arch theory is used in the analysis. Deflections are computed for arches with various lamination schemes and boundary conditions undergoing uniform and linearly varying temperature through the thickness. The effect of shallowness of the arch on the maximum deflection is studied.