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H. Assaee, M. Hajikazemi, H.R. Ovesy
Composite Structures, Volume 94, Issue 5, April 2012
Abstract
The effects of anisotropy (i.e. the ratio of longitudinal modulus of elasticity to transverse modulus of elasticity of a rectangular plate) on buckling and post-buckling performance of laminated plates under uniform end-shortening have been studied in this paper by implementing a Rayleigh–Ritz approach and a finite strip approach based on the concept of a rigorous post-buckling solution for composite plates and plate structures, namely the semi-energy approach. To validate the results, they are compared with those obtained from finite element method of analysis. The study of results has revealed that the buckling and post-buckling response of the laminates is significantly influenced by the changing of the anisotropy ratio.
Abstract:
In various fields of engineering, such as aerospace and marine engineering, composite laminated plates and plate structures are increasingly used as structural components. These structures are often employed in situations where they are subjected to in-plane compressive loading. Thus, it is important to accurately predict the buckling and post-buckling behavior of such structures. In aerospace, in particular, the quest for efficient and light-weight structures often leads to allowing for the possibility of buckling and post-buckling at the design load levels. The post-local-buckling behavior of elastic plates or plate structures is a geometrically non-linear problem. The non-linear large deflection behavior of a plate can be analyzed by solving the Von-Kármán non-linear equations, together with the appropriate boundary conditions. Unfortunately, the Von -Kármán equations are coupled and fourth-order and thus no rigorous solutions are available. In this regard, application of numerical or approximate methods is concerned by the engineers and researchers in the field. Determining the buckling load and the post-buckling equilibrium path is essential in design of abovementioned composite structures, especially, in early stage of design and in sizing phase. To find the optimum design in such phases, a large amount of configurations in lay-up arrangements and material properties should be analyzed as well as different geometries of plate structures, while computational economy must be granted. For the sake of computational economy it is suggested to lead the quest toward a fast analyzing tool which may reveal the buckling and post-buckling performance of composite plate structures with a fairly accurate margin. In the past couple of decades, development of fast analyzing tool has been received a great deal of attention by the researchers in structural engineering field. One of the methods which can reveal highly accurate results of buckling and post-buckling performance of composite plate structures is the Finite Strip Method. Different versions and so many novelties have been developed by the authors. In current paper the effects of anisotropy (i.e. the ratio of longitudinal modulus of elasticity to transverse modulus of elasticity of a rectangular plate) on buckling and post-buckling performance of laminated plates under uniform end-shortening have been studied in this paper by implementing a Rayleigh–Ritz approach and a finite strip approach based on the concept of a rigorous post-buckling solution for composite plates and plate structures, namely the semi-energy approach. To validate the results, they are compared with those obtained from finite element method of analysis. Study of the results has revealed that the buckling and post-buckling responses of the laminates are significantly influenced by the changing of the anisotropy ratio.
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