Abstract
In this paper, the linear eigen buckling and vibration analysis of various composite laminated structures such as flat plates, curved panels and cylindrical shell are investigated individually. The method of analysis is the semi-analytical finite strip approach which is based on the full-energy methods. The first-order Lagrange and the third-order Hermitian shape functions are utilized for the transverse and longitudinal directions, respectively, to estimate in-plane and out-of-plane displacements. By using layer-wise theory, thick structures can be modeled with good agreement with finite element methods as presented in this work. In addition, multiple nodes are considered along the thickness of structure, so displacement can be estimated more precisely in comparison with classic and first-order models as compared with other references.
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