Panel flutter characteristics of sandwich plates with CNT reinforced face sheets using an accurate higher-order theory

TL;DR

This study investigates the flutter behavior of sandwich panels with CNT-reinforced face sheets using a higher-order theory, revealing the influence of various parameters on flutter boundaries and modes.

Contribution

It introduces an accurate higher-order shear flexible element formulation for analyzing CNT-reinforced sandwich panels' flutter characteristics.

Findings

Higher-order model outperforms first-order theory in accuracy.

CNT volume fraction significantly affects flutter boundaries.

Parameters like thickness, aspect ratio, damping, and temperature influence flutter behavior.

Abstract

In this paper, the flutter characteristics of sandwich panels with carbon nanotube (CNT) reinforced face sheets are investigated using QUAD-8 shear flexible element developed based on higher-order structural theory. The formulation accounts for the realistic variation of the displacements through the thickness, the possible discontinuity in the slope at the interface, and the thickness stretch affecting the transverse deflection. The in-plane and rotary inertia terms are also included in the formulation. The first-order high Mach number approximation to linear potential flow theory is employed for evaluating the aerodynamic pressure. The solutions of the complex eigenvalue problem, developed based on Lagrange's equation of motion are obtained using the standard method for finding the eigenvalues. The accuracy of the present formulation is demonstrated considering the problems for which solutions are available. A detailed numerical study is carried out to bring out the efficacy of the higher-order model over the first-order theory and also to examine the influence of the volume fraction of the CNT, core-to-face sheet thickness, the plate thickness and the aspect ratio, damping and the temperature on the flutter boundaries and the associated vibration modes.