The frequency responses of free vibrated composite sandwich panel structure are investigated numerically by considering the geometrical nonlinearity via generalised Green–Lagrange strain kinematics in the framework of the equivalent single layer theory. The consistency and the accuracy of the current finite element solutions have been checked by solving a wide variety of examples taken as same as the reference. After the model standardisation, it is further extended to show the influence of various geometrical design parameters (side-to-thickness ratio, core-to-face thickness ratio, curvature ratio, lamination scheme and support condition) on the nonlinear frequencies of the sandwich composite flat/curved panel structure evaluated when computed using higher-order kinematic model. Also, the sandwich structural responses obtained using the equivalent higher-order kinematic model not only easy to implement but also the computational cost is low without hampering the accuracy of structural response.
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