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Research Papers

Aircraft Cabin Tonal Noise Alleviation Through Fuselage Skin Embedded Piezoelectric Actuators

[+] Author and Article Information
C. Testa

 INSEAN-CNR, Italian Ship Model Basin, Rome 00128, Italyc.testa@insean.it

G. Bernardini

Department of Mechanical and Industrial Engineering, University Roma Tre, Rome 00146, Italyg.bernardini@uniroma3.it

M. Gennaretti1

Department of Mechanical and Industrial Engineering, University Roma Tre, Via della Vasca Navale 79, Rome 00146, Italym.gennaretti@uniroma3.it

1

Corresponding author.

J. Vib. Acoust 133(5), 051009 (Sep 20, 2011) (10 pages) doi:10.1115/1.4003941 History: Received June 18, 2010; Revised February 01, 2011; Published August 31, 2011; Online September 20, 2011

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 actuation of the piezoelectric patches, aimed at alleviating the corresponding cabin noise. The aeroacoustoelastic plant model considered in the control problem is obtained by combining 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.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Shell coordinates system

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Figure 2

Sketch of smart shell patch with PZT embedded

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Figure 3

Top view of fuselage, microphones location and noise sources location

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Figure 4

Rear view of fuselage, microphones location and noise sources location

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Figure 5

Structural eigenfrequencies

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Figure 6

Acoustoelastic eigenfrequencies

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Figure 7

Radial displacement from in-plane loads

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Figure 8

Radial displacement from bending loads

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Figure 9

Radial displacement from symmetric PZT actuation

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Figure 10

Radial displacement from emisymmetric PZT actuation

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Figure 11

Sound level reduction from six-smart-patch control

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Figure 12

SPL reduction from eight-smart-patch control

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Figure 13

SPL reduction from ten-smart-patch control

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Figure 14

SPL reduction from ad hoc location of six-smart patches

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