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.
A. Bhimaraddi and K. Chandrashekhara, "Three-Dimensional Elasticity Solution for Static Response of Simply Supported Orthotropic Cylindrical Shells," Composite Structures, Elsevier, Jan 1992.
The definitive version is available at http://dx.doi.org/10.1016/0263-8223(92)90028-B
Mechanical and Aerospace Engineering
Article - Journal
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