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Research Papers

Non-Model-Based Identification of Delamination in Laminated Composite Plates Using a Continuously Scanning Laser Doppler Vibrometer System

[+] Author and Article Information
Da-Ming Chen

Department of Mechanical Engineering,
University of Maryland, Baltimore County,
1000 Hilltop Circle,
Baltimore, MD 21250

Y. F. Xu

Department of Mechanical and
Materials Engineering,
University of Cincinnati,
Cincinnati, OH 45221

W. D. Zhu

Department of Mechanical Engineering,
University of Maryland, Baltimore County,
1000 Hilltop Circle,
Baltimore, MD 21250
e-mail: wzhu@umbc.edu

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received August 11, 2017; final manuscript received December 7, 2017; published online February 22, 2018. Assoc. Editor: Huageng Luo.

J. Vib. Acoust 140(4), 041001 (Feb 22, 2018) (11 pages) Paper No: VIB-17-1364; doi: 10.1115/1.4038734 History: Received August 11, 2017; Revised December 07, 2017

Delamination frequently occurs in a laminated composite structure and can cause prominent local anomalies in curvature vibration shapes associated with vibration shapes of the composite structure. Spatially dense vibration shapes of a structure can be rapidly obtained by use of a continuously scanning laser Doppler vibrometer (CSLDV) system, which sweeps its laser spot over a vibrating surface of the structure. This paper introduces a continuous scanning scheme for general quadrangular scan areas assigned on plates and extends two damage identification methods for beams to identify delamination in laminated composite plates using a CSLDV system. One method is based on the technique that a curvature vibration shape from a polynomial that fits a vibration shape of a damaged structure can well approximate an associated curvature vibration shape of an undamaged structure and local anomalies caused by structural damage can be identified by comparing the curvature vibration shape of the damaged structure with that from the polynomial fit, and the other is based on the technique that a continuous wavelet transform can directly identify local anomalies in a curvature vibration shape caused by structural damage. The two methods yield corresponding damage indices and local anomalies in curvature vibration shapes can be identified in neighborhoods with high damage index values. Both numerical and experimental investigations on effectiveness of the two methods are conducted on a laminated composite plate with a delamination area. In the experimental investigation, delamination identification results from the two methods were compared with that from a C-scan image of the composite plate.

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Figures

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Fig. 2

(a) Horizontal scan trajectory (solid lines) and (b) a vertical scan trajectory (solid lines) on a rectangular plate (dashed lines)

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Fig. 1

(a) Components of a CSLDV system and (b) a simplified diagram of the CSLDV system

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Fig. 5

Dimensions of a six-laminate [0 deg/90 deg/0 deg]s IM-7 fiber-reinforced polymer composite plate with delamination. The delamination area is a square with the side length of 4.0 cm and located between the third and fourth laminates of the composite plate.

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Fig. 3

General quadrangular scan area with a horizontal scan trajectory

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Fig. 4

Voltage signals for the (a) X and (b) Y mirrors to generate the scan trajectory in Fig. 3

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Fig. 11

(a) Vibration shape of the composite plate at 89 Hz and (b) that of the plate at 150 Hz

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Fig. 6

(a) Mode shape of the second out-of-plane mode of the composite plate and (b) that of the fourth out-of-plane mode of the plate

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Fig. 7

(a) Simulated vertical scan trajectory on the composite plate for Znum,2 and (b) the simulated horizontal scan trajectory on the plate for Znum,4

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Fig. 8

(a) Curvature damage index associated with Zscan,2, (b) the curvature damage index associated with Zscan,4, and (c) the auxiliary curvature damage index associated with Zscan,2 and Zscan,4; nh = 0.005 m is used to calculate curvature vibration shapes

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Fig. 9

(a) Wavelet damage index associated with Zscan,2, (b) the wavelet damage index associated with Zscan,4, and (c) the auxiliary wavelet damage index associated with Zscan,2 and Zscan,4; s = 0.005 m is used to calculate wavelet transforms of mode shapes

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Fig. 10

(a) Fixture of the composite plate with delamination and (b) the test setup for measurement of vibration shapes of the plate, where “SLDV” stands for scanning laser Doppler vibrometer

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Fig. 12

(a) Curvature damage index associated with the mode shape at 89 Hz, (b) the curvature damage index associated with the mode shape at 150 Hz, and (c) the auxiliary curvature damage index associated with the two mode shapes; nh = 0.005 m was used to calculate curvature vibration shapes

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Fig. 13

(a) Wavelet damage index associated with the vibration shape at 89 Hz, (b) the wavelet damage index associated with the vibration shape at 150 Hz, and (c) the auxiliary wavelet damage index associated with the two vibration shapes; s = 0.005 m was used to calculate wavelet transforms of vibration shapes

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Fig. 14

C-scan image of the composite plate with delamination

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