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

Abstract

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.

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

“…All panels are subjected to sinusoidal distributed temperature field and have rectangular platform with a = b h/a = 0 1, and mechanical properties given in (34). It can be seen that the results obtained by the present method and analytical methods [10,15], are in good agreement in all cases and the results of the shell theory used in the present study provides results as accurate as the results obtained from the exact shell theory used in [15].…”

“…(15), the comparison of the results of solving laminated cylindrical and spherical shell panels with simply supported edges, that have already been solved analytically by Khare et al [10] and Khdeir [15], is presented here. The non-dimensional center deflection of 0/90 cylindrical and spherical shell panels and ten-layer 0/90 5 cylindrical shell panels with various R/a ratios obtained from higher-order shear deformation theories [10], and firstorder shear deformation theories [15], are presented in Table 2. All panels are subjected to sinusoidal distributed temperature field and have rectangular platform with a = b h/a = 0 1, and mechanical properties given in (34).…”

“…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. Khdeir [15] presented an analytical solution for cross-ply laminated doubly curved, spherical, and cylindrical shell panels based on a first-order shell theory proposed by Qatu [16] as an exact general shell theory and thermal deformations reported for boundary conditions with two opposite edges simply supported.…”

“…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].…”

Weak Formulation Study For Thermoelastic Buckling Analysis Of Thick Laminated Cylindrical Shells

“…A thermal bending analysis of doubly curved laminated shell panels with general boundary conditions and laminations is presented by Maghami and Tahani (2015). Khdeir (2012) investigated thermal deformations in cross-ply laminated shells by state space approach. The effect of the through-the-thickness temperature distribution on the response of layered and composite shells is calculated by Brischetto (2009).…”