本文根据无粘流体的非定常势流理论，推导出声源在亚声速不可压缩流场中对机翼产生的非定常流体动力的精确解，讨论了典型翼段上单极子声源的位置对声致气动载荷的影响，并通过对声－涡耦合的分析，解释了限于弱扰动的声激励消除颤振的机理，为有源声控制技术应用于流致振动和涡流的控制提供了理论基础。 According to the unsteady flow theory of non-viscous fluid, the exact solution of the unsteady hydrodynamic force generated by the sound source to the wing in unsteady sub-sonic flow field is deduced. The position of the monopole sound source on a typical wing segment On the aerodynamic loads, and through the analysis of the acoustic-vortex coupling, the mechanism of eliminating the flutter limited by the weak excitation is explained, which provides the theory for the application of the active acoustic control technology to the control of the flow induced vibration and the vortex flow basis.