| Реферат: | eng: Analytical solution of the buckling problem for a composite cylindrical sandwich panel subjected to axial load is presented in the paper. The straight longitudinal edges of the panel are fully clamped, and the curved sides are simply supported. This loading results in the biaxial compression of the panel. The buckling analysis is performed using the equations of the engineering theory of laminated cylindrical shells, taking into account the transverse shear deformations. The system of linearized buckling equations is derived in terms of unknown displacements, deflection, and angles of rotation of the normal to the middle surface of the panel. The equations are solved by combining the Levy and Galerkin methods. In this approach, the deformed panel was approximated by trigonometry and beam functions. The analytical formula for the critical load has been derived and verified using finite-element analysis. Based on this formula, the influence of Poisson’s effect on the value of buckling load has been studied. Design application of the formula is demonstrated for a specified value of the critical load. © The Author(s) 2019.
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| Цитирование: | 1. Lopatin AV, Morozov EV, Shatov AV., Buckling of uniaxially compressed composite anisogrid lattice cylindrical panel with clamped edges. Compos Struct 2017; 160: 765–772.
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