Vibration and Buckling Analysis of Multifunctional Antenna Structures with Thermoelastic Characteristics

Abstract

The performance of multifunctional antenna structure contained inside of the aircraft structure is analyzed under the influence of vibration caused by airflow and a thermal environment. The model is a multi-layer sandwich structure composed of carbon/epoxy, glass/epoxy and a dielectric polymer which is assumed to be an antenna. The First-order Shear Deformation Theory (FSDT) is used with a modified shear correction factor. In order to account for a geometrical nonlinearity, the governing equations are based on the von-Karman displacement-strain relationship with the principle of virtual work. Additionally, using the first-order piston theory, the effect of aerodynamic pressure is represented in the equation. The Newton-Rhapson iteration and the Newmark method is used to solve the nonlinear equation and the time analysis, respectively. Also, neutral surface and shear correction factor concepts are studied for unsymmetric models. The thermal environment is generally considered with one-dimensional heat conduction equations. To check the validity of the results, it is compared to the numerical data of vibration and buckling from previous studies. Post-buckling and flutter analysis is performed with simply-supported and clamped boundary conditions.