Optimal Design of Tonal Noise Control Inside Smart-Stiffened Fuselages of Turboprop Aircraft

In this paper the issue of the abatement of the tonal noise generated by propellers inside the fuselage of a general turboprop aircraft is addressed. The problem is analysed in a multidisciplinary context, involving interactions among exterior noise eld, elastic fuselage dynamics, interior acoustics and control system. A stiened fuselage, with piezoelectric patches embedded into the structure, is supposed to be impinged by the external sound wave generated by the propellers; an optimal LQR cyclic control formulation, coupled with a genetic optimization algorithm (GA), is applied for the synthesis of a control law driving smart actuators so as to alleviate cabin noise. The aeroacoustoelastic plant model considered in the control problem is obtained by combining a modal approach for the description of the acoustic eld within the cabin and the elastic displacement of the smart shell, with a Boundary Element Method (BEM) scattering modelling based on the Ffowcs Williams and Hawkings Equation (FWHE) for the prediction of exterior pressure disturbances. Considering a general aviation aircraft fuselage impinged by pressure disturbances emitted by a couple of pulsating point sources moving with it, numerical results examine the eectiveness and robusteness of the proposed active control law when synthesized through the proposed GA algorithm.

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