中文摘要：

二元刚性机翼结构简化为三自由度结构，在浮沉位移和俯仰位移方向的非线性刚度简化为立方非线性，对于控制截面存在间隙采用双线性刚度代替．基于靶能量转移的原理在机翼结构耦合非线性能量阱，实现对机翼颤振的抑制．考虑准定常气流，建立机翼减振前后的运动方程，通过数值模拟构造减振前后峰值一峰值图，初步反应其整体的减振效果．通过弧长数值连续法和结合Floquet算子构造减振前后的分岔图，并研究其稳定性．通过分岔图结合数值模拟的峰值图，讨沦在不同风速下的减振效果，结果表明机翼结构颤振可以部分甚至全部抑制．

英文摘要：

A 2-dimensional rigid airfoil with a control surface is simplified to 3-DOF aeroelastic model. This 3- DOF aeroelastic model took a cubic nonlinear stiffness in heaving and pitching displacement directions, and era- ployed bilinear stiffness for the clearance in the control surface. Based on the principle of target energy transfer, a single degree of nonlinear energy sink（NES） is coupled with the airfoil structure for suppressing the flutter of the system. Considering the quasisteady aerodynamic theory, the motion equations of the two systems （with and without NES） are established. Meanwhile, the peak-peak amplitude diagrams show that the global dynamic prop- erty of the system is changed by attaching a NES. Bifurcation diagrams is also constructed by using numerical con- tinuation method for both systems. The Comparison of the bifurcation diagrams exhibits the suppressing effect of the NES, and It is find that aeroelastic instability was partially or even completely suppressed by passively trans- ferring vibration energy from the wing to the NES in a one-way irreversible fashion.