湍流边界层（TBL）脉动压力与边界结构相互作用产生的噪声及控制问题是客机、高铁等高速运载工具中的一类基础性声学问题。本项研究拟以大型客机的座舱噪声控制为应用背景，以解决TBL脉动压力的在无流动环境下的实验模拟为目标，重点开展TBL脉动压力的阵列声源合成装置设计、建立与验证，并在此基础上，开展TBL脉动压力作用下飞机侧壁结构主被动阻尼控制方法和实验验证。本项研究取得的成果可为TBL脉动压力与边界结构相互作用产生的噪声及控制问题提供新的实验手段和降噪方法。

Coupling between a turbulence boundary layer (TBL) fluctuating pressure field and a boundary structure, as well as its induced structural noise and the relevant control methods, is one of the key issues in developing low-noise large aircraft, high-speed trains, and underwater vehicles. In the background of reducing the noise level in a commercial aircraft cabin, this project will aim at establishing an experimental device for the synthesis of TBL excitations and achieving TBL-induced vibro-acoustics test at the constraints of without flow, and based of which, developing passive/active control methods and validations for the nose transmission through typical aircraft side panels due to TBL excitations.