流固耦合翼型跨声速抖振载荷控制与机理分析OA

Transonic buffet can induce shock wave oscillations and flow separation,leading to lift fluctuations and in-creased structural dynamic responses,which necessitates load alleviation and response control.Based on small-amplitude skin vibration,this paper designs closed-loop active control laws with time delays to reduce lift fluctuations and structural responses in the plunge and pitch degrees of freedom of an airfoil under fluid-structure interaction.The influence of different control parameters is analyzed from the perspective of flow field evolution,with a focus on com-paring the transonic buffet responses and control effectiveness between the fluid-structure interaction mode and the forced vibration response mode.The results indicate that under the forced vibration mode,the optimal control perfor-mance is achieved with a control law delay time of 0.25 cycles and the skin vibration center located at 0.55 chord length.In this configuration,the suppression of flow separation is most effective,thereby mitigating shock wave mo-tion and achieving a buffet load reduction rate of 94.5%.Under fluid-structure interaction,the transonic buffet load re-duction rate is 91.8%.Compared to the forced vibration mode,the buffet load before control is larger,the buffet re-sponse frequency changes,and flow separation becomes more pronounced.