Thermal Stress Analysis of Laminated Doubly Curved Shells Using a Shear Flexible Finite Element

The thermal stress analysis oflaminated doubly curved shallow shells is presented using a shear flexible finite element model. The basic equations of the laminated shell theory are the extensions of Sanders\u27 shell theory to include shear deformation and the thermal strains. The present finite element solution for isotropic and composite plates is compared with the closed form solutions available in the literature. A wide variety of laminated shell problems subjected to different temperature fields are studied. The influence of temperature dependent material properties, panel sizes, and boundary conditions on the thermal deformations are demonstrated

Comparison of Elasticity, Shell Core, and Sandwich Shell Theories

the problem of an infinite circular sandwich shell subjected to an axisymmetric radial line load is investigated using three-dimensional elasticity theory, shell core method, and sandwich shell theory due to Fulton and Schmidt. A comparison of the stresses and displacements with an exact elasticity solution is carried out for various shell parameters in order to clearly bring out the limitations of sandwich shell theories of Fulton and Schmidt as well as the shell core solutions

Shell-Core Method for the Analysis of a Long Circular Cylindrical Sandwich Shell Subjected to Axisymmetric Loading

The analysis of a sandwich shell having a thick core and thin outer and inner layers (facings) and subjected to axisymmetric loads is considered. The problem is solved by applying the three-dimensional theory of elasticity to the core and the classical thin shell theory for the outer and inner facings. The displacement and stress continuity conditions are satisfied along the junctions of the facings and core. The results obtained from this solution have been compared with the results obtained from the sandwich shell theory of Fulton

Three-Dimensional Elasticity Solution for Static Response of Simply Supported Orthotropic Cylindrical Shells

This paper deals with the analysis of homogeneous and laminated cylindrical panels made of an orthotropic material, such as the fiber reinforced composites, using the three-dimensional elasticity equations. Solution is obtained by utilizing the assumption that the ratio of the panel thickness to its middle surface radius is negligible as compared to unity. However, it is shown that by sub-dividing the panel thickness into sub-layers of smaller thickness and matching the interface displacement and stress continuity conditions, very accurate results can be obtained. The two-dimensional shell theories have been compared for their accuracy in the light of the present three-dimensional elasticity analysis. Numerical results for some orthotropic panels show that the two-dimensional shell theories are very inaccurate when the thickness to length ratio of the panel is more than 1/20 . Also, it is observed that the predictions of the two-dimensional shell theories are relatively poor in the case of two-layered panels as compared to three-layered and homogeneous panels