Flutter characteristics of a rectangular sandwich plate with laminated three-phase polymer/GNP/fiber face sheets and an auxetic honeycomb core in yawed supersonic fluid flow

In the presented work, the flutter (aeroelastic stability) behavior of a sandwich plate under yawed supersonic fluid flow is investigated. The plate consists of an auxetic re-entrant honeycomb core and two laminated polymer-based composite face sheets reinforced with graphene nanoplatelets (GNPs) and fibers. The sinusoidal shear deformation theory (SSDT) and linear piston theory are utilized to model the plate and aerodynamic pressure, respectively. The governing equations and associated boundary conditions are derived utilizing Hamilton’s principle, and a numerical solution is performed via the differential quadrature method (DQM). The critical aerodynamic pressure is determined, and the effects of various parameters on the aeroelastic stability characteristics are examined such as the geometric parameters of the auxetic honeycomb core, mass fractions of the GNPs and the fibers, the thickness of the plate, and yaw angle. Numerical results reveal that by considering a specified total thickness for the plate, the critical aerodynamic pressure decreases by increasing the thickness of the auxetic honeycomb core. It is observed that the geometrical characteristics of the cells in the auxetic honeycomb core have no significant effect on the critical aerodynamic pressure.