Aircraft Cabin Tonal Noise Alleviation Through Fuselage Skin Embedded Piezoelectric Actuators

"\"An integrated spectral-integral formulation is applied for prediction and active control of. the noise generated by propellers inside the cabin of a general aviation aircraft. It. consists of a multidisciplinary approach that involves interaction among exterior noise. field, elastic fuselage dynamics, interior acoustics, and control system. A fuselage skin. embedding piezoelectric elements is supposed to be impinged by external sound waves. generated by propellers. An optimal harmonic control approach is applied for the actua-. tion of the piezoelectric patches, aimed at alleviating the corresponding cabin noise. The. aeroacoustoelastic plant model considered in the control problem is obtained by combin-. ing modal approaches for the description of cabin acoustic field and fuselage shell. dynamics, with a boundary element method scattering formulation for the prediction of. exterior pressure disturbances. Considering the fuselage of a general aviation aircraft. impinged by noise generated by a couple of pulsating point sources moving with it,. numerical results examine the effectiveness of the control approach applied to several. configurations of piezoelectric actuators. . \""