This paper describes preliminary laboratory experiments conducted on a turboprop aircraft fuselage to reduce interior cabin noise and vibration. Piezoelectric elements were grouped to construct a long onedimensional array of actuators bonded to the fuselage in the main sound transmission path, at the propeller footprint. Strain gauges and accelerometers were used as alternative sensor devices, and distributed along the actuator in a collocated arrangement. The array of actuators and sensors was designed to work in unison, generating a “smart” closed-loop array of control elements that possess wave-number filtering properties for the less critical acoustic tnodes of the cabin. The control system was tested in the laboratory under an elementary propeller pressure loading distribution. Promising results were obtained, as the closed-loop control system proved to be unconditionally stable, and able to significantly attenuate the fuselage vibration in the transmission path at the critical blade passage frequencies. Although only one array of control elements was used in a non-optimized arrangement, interior noise reduction was also observed during the tests, proving the merit of the concept.

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Conference AIAA/ASME/AHS Adaptive Structures Forum, 1996
Grewal, A. (A.), Nitzsche, F, Zimcik, D.G. (D. G.), & Leigh, B. (B.). (1996). Active control of aircraft cabin noise using smart structures. In AIAA/ASME/AHS Adaptive Structures Forum, 1996 (pp. 91–100). doi:10.2514/6.1996-1274