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Research Papers

Active Structural-Acoustic Control of Laminated Composite Truncated Conical Shells Using Smart Damping Treatment

[+] Author and Article Information
M. C. Ray

Department of Mechanical Engineering,
Indian Institute of Technology,
Kharagpur 721302, India

Contributed by the Design and Engineering Division of ASME for publication in the Journal of Vibration and Acoustics. Manuscript received December 15, 2010; final manuscript received August 24, 2012; published online February 25, 2013. Assoc. Editor: Michael Brennan.

J. Vib. Acoust 135(2), 021001 (Feb 25, 2013) (13 pages) Paper No: VIB-10-1300; doi: 10.1115/1.4023046 History: Received December 15, 2010; Revised August 24, 2012

This article deals with the active structural-acoustic control of composite truncated circular conical shells using active constrained layer damping (ACLD) treatment. The constraining layer of the ACLD treatment is made of vertically/obliquely reinforced 1–3 piezoelectric composite (PZC) material. A finite element model of smart laminated truncated conical shells backed by the acoustic cavity and integrated with the patches of such ACLD treatment has been developed to demonstrate the performance of these patches for active structural-acoustic control of symmetric and antisymmetric cross-ply and antisymmetric angle-ply truncated conical laminated shells. Both velocity and pressure rate feedback control laws have been implemented to activate the patches. Particular emphasis has also been placed on investigating the effect of variation of piezoelectric fiber orientation angle in the constraining layer on the performance of the patches.

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Figures

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Fig. 1

Schematic diagram of the laminae of vertically/obliquely reinforced 1–3 piezoelectric composites: (a) piezoelectric fibers are coplanar with the vertical xz-plane, (b) piezoelectric fibers are coplanar with the vertical yz-plane

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Fig. 2

Schematic representation of a laminated truncated conical shell integrated with the patches of ACLD treatment and coupled with the acoustic cavity

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Fig. 3

Deformations of transverse cross-sections of the laminated shell integrated with the ACLD treatment, which are parallel to (a) xz-plane and (b) yz-plane

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Fig. 4

Frequency response for the deflection of an antisymmetric angle-ply (45 deg/-45 deg) truncated conical shell-cavity system implementing (a) velocity feedback control and (b) pressure rate feedback control (ψ=0 deg)

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Fig. 5

Frequency response for the SPL of the antisymmetric angle-ply (45 deg/-45 deg) truncated conical shell-cavity system implementing (a) velocity feedback control and (b) pressure rate feedback control (ψ=0 deg)

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Fig. 6

Frequency responses for the symmetric cross-ply (0 deg/90 deg/90 deg/0 deg) truncated conical shell-cavity system: (a) deflection implementing velocity feedback control and (b) SPL implementing pressure rate feedback control (ψ=0 deg)

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Fig. 7

Frequency responses for the antisymmetric cross-ply (0 deg/90 deg/0 deg/90 deg) truncated conical shell-cavity system: (a) deflection implementing velocity feedback control and (b) SPL implementing pressure rate feedback control (ψ=0 deg)

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Fig. 8

SPL distribution at the x1z1-plane, with y1=0 and passing through the point (-0.4, 0, 0.128) inside the cavity (a) before control (Kd=0) and (b) after control (Kd=1600), employing velocity feedback when the symmetric cross-ply (0 deg/90 deg/90 deg/0 deg) truncated conical shell vibrates at fundamental frequency 332Hz(ψ=0 deg)

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Fig. 10

Effect of variation of piezoelectric fiber orientation angle (ψ) on the (a) deflection (Kd=1600) and (b) SPL (Kd=0.001) of the truncated conical shell-cavity system (45 deg/-45 deg) when the piezoelectric fibers of the constraining layer are coplanar with yz-plane

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Fig. 11

Effect of variation of piezoelectric fiber orientation angle (ψ) on the (a) deflection (Kd=1600) and (b) SPL (Kd=1600) of the truncated conical shell-cavity system (0 deg/90 deg/90 deg/0 deg) when the piezoelectric fibers of the constraining layer are coplanar with xz-plane

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Fig. 12

Effect of variation of piezoelectric fiber orientation angle (ψ) on the (a) deflection (Kd=1600) and (b) SPL (Kd=1600) of the truncated conical shell-cavity system (0 deg/90 deg/90 deg/0 deg) when the piezoelectric fibers of the constraining layer are coplanar with yz-plane

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Fig. 9

Effect of variation of piezoelectric fiber orientation angle (ψ) on the (a) deflection (Kd=1600) and (b) SPL (Kd=0.001) of the truncated conical shell-cavity system (45 deg/-45 deg) when the piezoelectric fibers of the constraining layer are coplanar with xz-plane

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