Thermal Stresses of Weak Formulation Study for Thick Open Laminated Shell

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

“…Ding [13] presented weak formulations of mixed-state equations including boundary conditions of an open laminated cylindrical shell. Brischetto and Carrera [14] studied uncoupled thermal stress problem of multilayered composite shells assuming a linear distribution of temperature through the thickness for laminated cylindrical and spherical shells.…”

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. KHDEIR anisotropic structures are presented in [6,7]. Thermal stresses mixed state equation of an open cylindrical shell is established in [8].…”

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.