Nonlinear vibration characteristic of FGM sandwich cylindrical panel with auxetic core subjected to the temperature gradient

This study deal with the nonlinear vibration of sandwich panel, composed of functionally graded material (FGM) skins and double U auxetic core subjected to heat conduction. The nonlinear equations are obtained by applying Hamilton's principles in framework higher order shear deformation theory (HSDT) and von Karman's nonlinear theory. Linear and nonlinear equations of motion are solved by applying the differential quadrature method (DQM) and homotopy perturbation technique, respectively. In the numerical illustration, at first validation of the present formulation is carried out by comparing the numerical results with those available in the open literature. Then the effects of several parameters such as geometric parameters of auxetic core, power-law exponent, different boundary conditions, and temperature gradient on the nonlinear frequencies of sandwich panel are studied. Finally, the important findings of this research indicate that the ratio of core thickness, inclined angle, and thickness to inclined length have significant effects on nonlinear frequency response. Based on the results of this article designers can development of different parts of aircraft. (c) 2023 Elsevier B.V. All rights reserved.

Automated summary

This study investigates the nonlinear vibration of a sandwich panel composed of functionally graded material (FGM) skins and double U auxetic core under heat conduction. Nonlinear equations are derived using Hamilton's principles and von Karman's nonlinear theory. The linear and nonlinear equations of motion are solved using the differential quadrature method (DQM) and homotopy perturbation technique respectively. The research findings demonstrate the significant effects of core thickness ratio, inclined angle, and thickness to inclined length ratio on the nonlinear frequency response of the sandwich panel. The results of this study can contribute to the development of different aircraft components.