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In this paper, an approximate solution using layer-wise theory for the vibration analysis of rotating laminated cylindrical shells with ring and stringer stiffeners under axial load and pressure is presented. The cylindrical shells are stiffened with uniform interval and it is assumed that the stiffeners have the same material and geometric properties and cylindrical shell reinforced by outer stiffeners while stiffeners are treated as discrete elements. The equations of motion are derived by the Hamilton’s principle. In deriving the governing equations three-dimensional elasticity theory are used and the study includes the effects of the Coriolis and centrifugal accelerations and the initial hoop tension. The layer-wise theory is used to discretize the equations of motion and the related boundary conditions through the thickness of the shells. The edges of the shell are restrained by simply supported boundary conditions. The presented results are compared with those available in the literature and also with the FE results and excellent agreement is observed. Finally, the results obtained include the relationship between frequency characteristics of stiffened cylindrical shell and different geometry of stiffeners, stiffener type, rotating velocities, amplitude of pressure and amplitude of axial load.

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In the present paper, a new combined technique consist of experimental results and numerical solution for determination of elastic constants of thin and thick orthotropic plates with various stacking sequences; and also isotropic plates under different boundary conditions is proposed. This new proposed technique makes use of vibrational test data, corresponding numerical solution and optimization methods. The vibration test data consists of a set of eigen frequencies that are obtained from transverse vibration test of the plate. The numerical solution is based on a finite element method using a commercial program. Material constants of the plate are determined by using of the inverse method and a particle swarm optimization algorithm in MATLAB software. The error function is based on the sum of square difference between experimental data and numerical data of eigen frequencies solution. The validation, performance and ability of the proposed technique in this paper are discussed using experimental and numerical data available in the literature. The higher accuracy of results that obtained by the present method in comparison with other methods proved the validity and capability f the new proposed method.

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The optimal design of multilayer substrates containing the cutout under compression is very important to achieve maximum buckling resistance in comparison with structural weight, especially in aerospace structures. In this study, buckling and post-buckling behavior of composite laminated plates with orthogonal and symmetrical layup containing the cutout with different diameters has been investigated experimentally, semi-analytically, and numerically. To study the buckling of the composite plate with cutout semi-analytically, a finite strip method is developed. A finite element method was used for numerical analysis. The required material parameters for modeling were obtained from standard tests. The results of the current study show that the size of diameter of cutout does not have considerable effect on elastic rigidity of plate, but the buckling load significantly decreases by increasing cutout diameter. Also, buckling load and elastic rigidity of plate are considerably increased by increasing the number of composite layers. The thickness of plate has more effect on buckling load than the diameter of hole. Studies show that there is a good match between the results of buckling behavior derived from semi-analytical and finite element methods with experimental results.