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. 2022 Jan 5;15(1):394.
doi: 10.3390/ma15010394.

Transverse Cracking Induced Acoustic Emission in Carbon Fiber-Epoxy Matrix Composite Laminates

Zeina Hamam  1 , Nathalie Godin  1 , Pascal Reynaud  1 , Claudio Fusco  1 , Nicolas Carrère  2 , Aurélien Doitrand  1
Affiliations

Transverse Cracking Induced Acoustic Emission in Carbon Fiber-Epoxy Matrix Composite Laminates

Zeina Hamam et al. Materials (Basel). .

Abstract

Transverse cracking induced acoustic emission in carbon fiber/epoxy matrix composite laminates is studied both experimentally and numerically. The influence of the type of sensor, specimen thickness and ply stacking sequence is investigated. The frequency content corresponding to the same damage mechanism differs significantly depending on the sensor and the stacking sequence. However, the frequency centroid does not wholly depend on the ply thickness except for the inner ply crack and a sensor located close enough to the crack. Outer ply cracking exhibits signals with a low-frequency content, not depending much on the ply thickness, contrary to inner ply cracking, for which the frequency content is higher and more dependent on the ply thickness. Frequency peaks and frequency centroids obtained experimentally are well captured by numerical simulations of the transverse cracking induced acoustic emission for different ply thicknesses.

Keywords: acoustic emission; carbon fiber/epoxy matrix composites; laminate transverse cracking; numerical simulation.

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Conflict of interest statement

The authors declare no conflict of interest.

Figures

Figure 1
Figure 1
(a) Location of the sensors on the specimen (b) Frequency sensitivity functions of picoHF and micro80 sensors used to capture acoustic emission during tensile tests in composite laminates (calibration curve obtained on steel block with reciprocity method).
Figure 2
Figure 2
Dimensions of the modeled specimens. Transverse cracking occurs in a 90 deg. Ply with respect to the loading direction.
Figure 3
Figure 3
Damping coefficient as a function of the frequency obtained experimentally for (i) emitted chirp and (ii) pencil lead break and (iii) numerically.
Figure 4
Figure 4
Cumulated localized signal number and stress as a function of strain for (a) [0/90/0] and [03/903/03] specimens using the micro80 sensor and (b) micro80 and picoHF sensors for [0/90/0] specimens.
Figure 5
Figure 5
(a) Frequency centroid and (b) peak frequency as a function of strain obtained for the [0/90/0] specimen (thickness = 0.9 mm) with either micro80 or picoHF sensors.
Figure 6
Figure 6
(a) Amplitude and (b) frequency centroid as a function of strain obtained with micro80 sensor for [0/90/0] or [03/903/03] specimens.
Figure 7
Figure 7
(a) Frequency centroid and (b) peak frequency as a function of the distance between the AE source and the micro80 sensors obtained experimentally for the [03/903/03] specimen and numerically.
Figure 8
Figure 8
(a) Frequency centroid (b) peak frequency as a function of the distance between the AE source and the micro80 sensors obtained experimentally for the [0/90/0] specimen and numerically.
Figure 9
Figure 9
(a) Frequency centroid (b) peak frequency as a function distance between the AE source and the picoHF sensors obtained experimentally for the [0/90/0] specimen and numerically.
Figure 10
Figure 10
Out-of-plane velocity as a function of time obtained at crack epicenter for (a) outer ply transverse cracking in [90n/0n/90n] specimens and (b) inner ply transverse cracking in [0n/90n/0n], (n = 1 or 3).
Figure 11
Figure 11
(a) Frequency centroid, (b) 1000–1500 kHz, (c) [500–1000] kHz and (d) 0–250 kHz partial powers as a function of distance between the source and the sensor obtained numerically for [0n/90 n/0 n] and [90n/0n/90n] stacking sequences (n = 1 or 3).
Figure 12
Figure 12
Simulated dispersion curves (wavenumber k as a function of frequency f) using 2D-FFT of signals recorded along a straight line perpendicular to the crack surface on the specimen top surface for (a) [0/90/0], (b) [03/903/03], (c) [90/0/90] and (d) [903/03/903] specimens.
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