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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-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,讨论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.
Binary rigid wing structure is simplified to three degrees of freedom structure, the nonlinear stiffness in the direction of drifting displacement and pitch displacement is simplified as cubic nonlinearity, and the bilinear stiffness is used instead of the clearance in control cross section.Based on the principle of target energy transfer, The wing structure is coupled with a nonlinear energy trap to suppress the flutter of the wing.According to the quasi-steady airflow, the equations of motion before and after the damping of the wing are established, and the peak-peak values before and after vibration damping are constructed by numerical simulation, Vibration effect.And the bifurcation diagram before and after vibration damping is constructed by arc-length numerical continuous method and Floquet operator, and its stability is studied.The damping effect under different wind speeds is discussed by the bifurcation diagram combined with the numerical simulation of the peak diagram, The results show that wing structure flutter can be partially or even completely suppressed.