Suppression of panel flutter response in supersonic airflow using a nonlinear vibration absorber

A nonlinear vibration absorber (NVA) is used to suppress the nonlinear response of a panel flutter in supersonic airflow. The nonlinear aeroelastic equations of a three-dimensional (3-D) panel with an NVA are established using Galerkin's method, with the aerodynamic load being based on the piston aerodynamic theory. We use the aeroelastic equations to study the nonlinear aeroelastic response behaviors of the 3-D panel with an NVA and then obtain the NVA suppression region. The effects of different NVA parameters on the flutter boundary and the NVA suppression region are examined, and a design technique is developed to find a suitable combination of parameter values to suppress the nonlinear panel flutter response. The results show that the nonlinear aeroelastic responses of the panel are completely suppressed by recurrent transient resonance capture (TRC) and permanent resonance capture (PRC) of the NVA in the NVA suppression region. The phase difference between the transient energy of the panel and the NVA is nearly 180 degrees in PRC. The NVA can suppress the aeroelastic response amplitude of the panel sufficiently only if the transient energy of the panel and NVA are comparable. The NVA parameters can affect the flutter boundaries and the NVA suppression regions with different patterns. The expected suppression response amplitude should be considered in designing the NVA parameters.

Automated summary

This study focuses on using NVA to suppress the nonlinear response of panel flutter in supersonic airflow. The effects of NVA parameters on flutter boundaries and suppression regions are examined, leading to the development of a design technique for finding suitable parameter values to suppress nonlinear panel flutter response.