Abstract
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.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
More From: Communications in Nonlinear Science and Numerical Simulation
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.