Abstract
A nonlinear energy sink (NES) is used to suppress panel flutter. A nonlinear aeroelastic model for a two-dimensional flat panel with an NES in supersonic flow is established using the Galerkin method. First-order piston aerodynamic theory is adopted to build the aerodynamic load. The effects of NES parameters on flutter boundaries of the panel are investigated using Lyapunov’s indirect method. The mechanism of the NES suppression of panel flutter is studied through energy analysis. Effects of NES parameters on aeroelastic responses of the panel are obtained, and a design technique is adopted to find a suitable combination of parameter values of the NES that suppresses the panel flutter effectively. Results show that the NES can increase or reduce the onset dynamic pressure of the panel flutter and it can reduce the aeroelastic response amplitude effectively within a certain range of dynamic pressure behind the onset dynamic pressure. The installation position of the NES depends on the direction of the airflow. The robust characteristics should be considered to find the suitable combination of parameter values of the NES.
Highlights
Panel flutter, which is a type of dynamic aeroelastic instability resulting from the interaction of aerodynamic, inertial, and elastic forces, can be described as a self-excited oscillation of the external skin panel of a flight vehicle with one side exposed to, usually, supersonic or hypersonic airflow
It is seen that the nonlinear energy sink (NES) can drive the panel to the equilibrium position more quickly than that without an NES
In region A, the response of the panel with or without NES converges to its equilibrium position; the NES can drive the panel to the equilibrium position more rapidly
Summary
Panel flutter, which is a type of dynamic aeroelastic instability resulting from the interaction of aerodynamic, inertial, and elastic forces, can be described as a self-excited oscillation of the external skin panel of a flight vehicle with one side exposed to, usually, supersonic or hypersonic airflow. This work proposes a passive control strategy, namely, the use of a nonlinear energy sink (NES), to suppress panel flutter or reduce the aeroelastic response of the panel. Georgiades and Vakakis [17] first attached the NES to a continuous primary vibration system (a linear beam structure) and proposed that the NES could be applied to the suppression of structural dynamic instabilities, such as limit cycle oscillations and flutter. Zhang et al [29] applied the NES to a flat panel aeroelastic system; they only investigated the preflutter responses and showed that the NES can reduce the vibration amplitude of the plate quickly.
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