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Tiltrotor cabin noise control through smart actuators.

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Title: Tiltrotor cabin noise control through smart actuators.
Authors: Bernardini, G.1, Testa, C.2, Gennaretti, M.1 m.gennaretti@uniroma3.it
Source: Journal of Vibration & Control. Jan2016, Vol. 22 Issue 1, p3-17. 15p.
Subjects: Intelligent actuators, Noise control, Optimal designs (Statistics), Aeroelasticity, Tilt rotor aircraft
Abstract: This paper deals with the abatement of the tonal noise inside the fuselage of a mid-range tiltrotor aircraft, as generated by the propulsive system. The problem is basically multidisciplinary, involving interactions among the exterior noise field, elastic fuselage dynamics, interior acoustics and control system. A stiffened fuselage, with piezoelectric patches embedded into the structure, is supposed to be impinged on by the aeroacoustic field generated by propellers and excited by the wing/pylon/proprotor vibratory loads at the wing–fuselage attachment. An optimal linear quadratic regulator cyclic control formulation, coupled with a genetic optimization algorithm, is applied to synthesize the control law driving the smart actuators so as to alleviate cabin noise. The aeroacoustoelastic model considered in the control problem is obtained by combining cabin interior acoustics, fuselage smart shell dynamics and wing/pylon/proprotor aeroelasticity described through modal approaches with the exterior pressure field provided by boundary element method solvers. Numerical results examine the effectiveness and robustness of the proposed active control strategy. [ABSTRACT FROM AUTHOR]
Copyright of Journal of Vibration & Control is the property of Sage Publications, Ltd. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
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DbLabel: Engineering Source
An: 112017413
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PubTypeId: academicJournal
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  Data: <searchLink fieldCode="AR" term="%22Bernardini%2C+G%2E%22">Bernardini, G.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Testa%2C+C%2E%22">Testa, C.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Gennaretti%2C+M%2E%22">Gennaretti, M.</searchLink><relatesTo>1</relatesTo><i> m.gennaretti@uniroma3.it</i>
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  Data: <searchLink fieldCode="DE" term="%22Intelligent+actuators%22">Intelligent actuators</searchLink><br /><searchLink fieldCode="DE" term="%22Noise+control%22">Noise control</searchLink><br /><searchLink fieldCode="DE" term="%22Optimal+designs+%28Statistics%29%22">Optimal designs (Statistics)</searchLink><br /><searchLink fieldCode="DE" term="%22Aeroelasticity%22">Aeroelasticity</searchLink><br /><searchLink fieldCode="DE" term="%22Tilt+rotor+aircraft%22">Tilt rotor aircraft</searchLink>
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  Data: This paper deals with the abatement of the tonal noise inside the fuselage of a mid-range tiltrotor aircraft, as generated by the propulsive system. The problem is basically multidisciplinary, involving interactions among the exterior noise field, elastic fuselage dynamics, interior acoustics and control system. A stiffened fuselage, with piezoelectric patches embedded into the structure, is supposed to be impinged on by the aeroacoustic field generated by propellers and excited by the wing/pylon/proprotor vibratory loads at the wing–fuselage attachment. An optimal linear quadratic regulator cyclic control formulation, coupled with a genetic optimization algorithm, is applied to synthesize the control law driving the smart actuators so as to alleviate cabin noise. The aeroacoustoelastic model considered in the control problem is obtained by combining cabin interior acoustics, fuselage smart shell dynamics and wing/pylon/proprotor aeroelasticity described through modal approaches with the exterior pressure field provided by boundary element method solvers. Numerical results examine the effectiveness and robustness of the proposed active control strategy. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Journal of Vibration & Control is the property of Sage Publications, Ltd. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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        Value: 10.1177/1077546314526919
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      – Code: eng
        Text: English
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        PageCount: 15
        StartPage: 3
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      – SubjectFull: Intelligent actuators
        Type: general
      – SubjectFull: Noise control
        Type: general
      – SubjectFull: Optimal designs (Statistics)
        Type: general
      – SubjectFull: Aeroelasticity
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      – SubjectFull: Tilt rotor aircraft
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      – TitleFull: Tiltrotor cabin noise control through smart actuators.
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              Text: Jan2016
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