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Delamination Localization in Sandwich Skin Using Lamb Waves by Finite Element Method.

1. Introduction

A sandwich composite is a materiel made from two thin skins bonded to a thick core. The skin studied in this paper is an orthotropic plate [[0].sub.4] with three mutually perpendicular planes of symmetry. The sandwich materials are designed to improve mechanical proprieties of structures. They are widely used in different fields especially in aeronautic industry. Their proprieties are influenced by the proportions of the matrix and the reinforcements. There are other parameters that also affect their characteristics like size, orientation, and distribution of the fibre. However, the heterogeneity of the composites structures leads to their weakness and facilitates the appearance of internal and external damage such as fibre breakage, matrix cracking, through-thickness hole, local delamination. Among these types of damage, delamination is especially easy to appear because the transverse tensile and interlaminar shear strengths are weak compared to the inplane strength [1]. The delamination causes wave scattering, mode conversion, and multiple reflections. To understand these mechanisms, theoretical, numerical, and experimental studies are conducted.

Feng, Lopes Ribeiro, and Geirinhas Ramos [2] analysed the interaction of symmetric [S.sub.0] and antisymmetric [A.sub.0] mode with the delamination using finite element simulations. The Lamb waves propagation in a 4-layer [[0/90].sub.s] laminate were compared with propagations obtained in 1-layer [0] and in 3-layer [90/90/0] sublaminates. Chiua, Roseb, and Nadarajaha [3] investigated the scattering of the [S.sub.0] mode by a delamination in quasi-isotropic fibre-composite laminate. Guo and Cawley [4] studied by finite element analysis and by experiment the interaction of the [S.sub.0] Lamb mode with delamination. Nadarajah, Vien, and Chiu [5] presented results for the scatter field for various angles of incidence and for varying defect sizes. Hayashi and Kawashima [6] studied the reflections of Lamb waves at a delamination by semianalytical finite element method. Ching-Tai and Veidta [7] investigated the scattering characteristics of [A.sub.0] mode Lamb wave at a delamination in a quasi-isotropic composite laminate. Bin [8] suggested an algorithm to localize and identify the damage in Woven Glass Fibre reinforced epoxy (WGF/epoxy). Mustapha [9] characterized fundamental symmetric and antisymmetric Lamb modes in terms of their velocity and magnitude variation as they change gradually in the thickness of a composite sandwich plate with a high density foam core. Ng [10] presented a theoretical and finite element (FE) investigation of the scattering characteristics of [A.sub.0] at delaminations in a quasi-isotropic composite laminate. Veidt and Ng [11] studied the influence of stacking sequence on fundamental antisymmetric Lamb wave ([A.sub.0]) scattering characteristics through holes in composite laminates. Luca [12] developed a valid finite element model to simulate Lamb waves' propagation in a Carbon Fibre Reinforced Plastic (CFRP) laminate for damage detection purpose and investigated the effects of the wave interaction with respect to damage parameters such as size and orientation. Yang [13] investigated some aspects of numerical simulation of excitation and detection of Lamb waves using piezoelectric disks in plate-like composite laminates.

In this paper, a numerical approach is proposed to localize a delamination in sandwich skin as presented in Figure 1. The aim of this work is to study the conversion by identifying the propagating modes and also to evaluate the symmetric and asymmetric delamination.

2. Lamb Waves Theory

Lamb waves are most used for many reasons; they can propagate long distances alongplates and shells so they permit quick inspection of large structures, and also they are sensitive to the small variations either in material proprieties or in structure of the plate. However, they are dispersive which means that the interpretation of received signals can be complicated. So the key is to choose one pure mode to excite and to analyse its reflection, conversion, and transmission.

2.1. Equation of Lamb Waves Propagation in Unidirectional Lamina. The characteristic equations of the symmetrical and antisymmetric waves are [14]

[mathematical expression not reproducible] (1)

with [D.sub.r] coefficients calculated by the following equations:

[mathematical expression not reproducible] (2)

[W.sub.r] = ([rho][c.sup.2] - [C.sub.11] - [C.sub.55][[alpha].sup.2.sub.r])/([C.sub.13] + [C.sub.55])[[alpha].sub.r]. For r {1, 2, 3, and 4}, with

[mathematical expression not reproducible] (3)

coefficients A, B and C are calculated by the following equations:

[mathematical expression not reproducible] (4)

where h is the skin thickness, k is the wavenumber corresponding to the X direction, c is the phase velocity. [C.sub.11], [C.sub.13], [C.sub.33], [C.sub.44], [C.sub.55], [C.sub.66] are the elastic constants, and [rho] is the skin density.

2.2. Dispersion Curves. The dispersion curves presented in Figure 2 for orthotropic plate [[0].sub.4] are plotted using DISPERSE program [15] in terms of wavenumber versus frequency.

At low frequency, two modes, [A.sub.0] and [S.sub.0], can propagate. As the frequency increases, more modes are possible to propagate.

2.3. Lamb Waves Control Technics. Among the contact technics to generate and to receive the signal, we find two methods: pitch catch and pulse echo. These two technics are simple but they require the coupling medium which limits the transmission of acoustic power.

In the pulse-echo method, the reflected signal permits evaluating the damage. In the pitch catch technic the transducer placed in the transmission side permits evaluating the defect. In this paper two methods have been used to evaluate the delamination.

3. Postprocess Tools

3.1. 2D-FFT Analysis. Lamb waves' propagation is sinusoidal in the frequency and spatial domains. For that reason, a temporal Fourier Transform is applied to go from the time to frequency domain; after that, a spatial Fourier Transform is computed to obtain the frequency wavenumber domain; see [16]. In practice, carrying out a spatial Fourier method to data obtained experimentally or numerically requires applying a 2D-FFT, using the following.

[mathematical expression not reproducible] (5)

3.2. Wavelet Analysis. Wavelet transform is an important tool in the time frequency domain of transient signals. The continuous wavelet transform of signal u(t) is defined as follows.

[mathematical expression not reproducible] (6)

The obtained signal is a function of a and b, the translation and scale parameters, respectively. The parameter psi (t) is the transforming function named the mother wavelet. In this paper we use wavelet transform by "gaus1" to locate the peak which permits determining the arrival time of the wave at specific frequency. Moreover, for each frequency f, the localization of maximal value of the wavelet coefficients cwt(a, b) allows identifying the arrival times [t.sub.1] and [t.sub.2]. Knowing the group velocity and the delay (delta) [DELTA]t = [t.sub.2] - [t.sub.1] between the two modes with the same nature, we can calculate the distance by the following equation.

[DELTA]x = [V.sub.g][DELTA]t (7)

Knowing the delay between two different modes (symmetric and antisymmetric), we calculate the distance by the following equation:

[DELTA]x = [DELTA][V.sub.g][DELTA]t (8)


[DELTA][V.sub.g] = [V.sub.S][V.sub.A]/[[V.sub.S] - [V.sub.A]]. (9)

Here [V.sub.S] and [V.sub.A] are the group velocities, respectively, of [S.sub.0] and [A.sub.0] modes. Arrival time method was used by many authors to localize the delamination; see [17].

4. Numerical Model Using FEM

Numerical simulations were carried out using finite element software ABAQUS to predict the [A.sub.0] Lamb wave propagation behaviour in a [[0].sub.4] plate. A number of modelling methods had been used by previous researchers to model the propagating wave: finite difference, boundary elements, strip elements, hybrid and finite element. The finite element method has been extensively and successfully used to model the Lamb waves and study their interactions with defects in structures [18]. Many researchers have used the numerical simulation to study Lamb waves. Chiua, Roseb, and Nadarajaha [3] built a 3D model in ABAQUS of the 8-ply laminate [[45/-45/0/90].sub.S]. Guo and Cawley [4] investigated the influence of delamination position through the thickness and its interaction with the [S.sub.0] mode using finite element analysis. The composite laminate modelled was the eight-layer cross-ply. Nadarajah, Vien, and Chiu [5] studied the scattering of a zero-order antisymmetric ([A.sub.0]) Lamb wave mode by semicircular mid-plane edge delamination using the commercial FE package ABAQUS. Hayashi and Kawashima [6] studied Lamb waves' propagation in laminated plates with delamination using the Strip Element Method and discussed the reflection and transmission for the case [S.sub.0] and [A.sub.0] excitation. Ng [10] modelled the delamination as a volume split in quasi-isotropic plate. The FE results were carried out by the explicit FE code LS-DYNA. Ng and Veidta [7] used a three-dimensional FE method to simulate an eight-ply [45/-45/0/90]S quasi-isotropic composite laminate with a delamination. The simulations were computed by ANSYS software. Panda [19] presented 3D FE simulations that were carried out to visualize the wave propagation and their interaction with the defect at various depths of an 8-layered Glass Fibre Reinforced Polymer (GFRP) by finite element software ABAQUS/Explicit. Ramadas [20] investigated the interaction of the primary antisymmetric mode [A.sub.0] with symmetric delamination type defects in a quasi-isotropic laminated composite using 2D model ANSYS. Soleimanpour and Ng [21] used 3D explicit finite element method to study cross-ply laminated composite beams [[0/90/0/90].sub.S]; they investigated the mode conversion and scattering characteristics of guided waves at delamination. Gudimetla and Kharidi [22] showed a procedure to simulate the propagation of Lamb waves in 8-layered Carbon Reinforced Fibre Plastic (CRFP) using a 2D model in ANSYS. The authors simulate the propagating Lamb waves along the plane of the structure in the form of a time dependent force excitation. Basri and Chiu [18] investigated how Lamb waves respond to the presence of material degradation in a plate-like structure using a series of finite element analyses. The propagation of these guided waves was interpreted with the dispersion characteristics, and displacement profiles were analysed in the frequency and wavenumber domain.

In this paper we try to predict the interaction of [A.sub.0] mode in orthotropic plate. The 2D numerical simulations were carried out using ABAQUS CAE. We consider the Lamb waves propagation only in the skin to simplify the propagating modes identification. This assumption has been made in many papers [23-25]. They consider only the propagation in skin as its acoustic impedance is more than the acoustic impedance of the core.

The skin has a length of L=400 mm and a thickness of h = 1.6 mm. The mechanical properties of each lamina are shown in Table 1. Once the geometry of the plate has been achieved, it remains to mesh and to define a sampling sufficient time.

4.1. Meshing and Time Sampling. To satisfy an accurate solution, the model has been meshed using (10), and the time step is calculated by (11).

max([DELTA]x, [DELTA]y) < [[lambda].sub.min]/10 (10)

[DELTA]t < 0.7 max([DELTA]x, [DELTA]y)/[V.sub.L] (11)

4.2. Excitation. In order to identify accurately the propagating modes, the simulation is performed on the range of frequencies to prevent dispersive phenomenon. For that reason we choose 300 kHz as frequency of excitation (see Figure 3).

5. Localization Method

The finite element method with ABAQUS CAE code is used to compute the temporal displacement by 2D-FFT technic (5) so as to identify the propagating and converted modes. Once the modes are identified, the next step consists in calculating the arrival times by WT (6). So there are two cases: in the first case, where there is no modes conversion, the time delay permits calculating the delamination position by (7); in the second case, where the mode converts to another ([A.sub.0] to [S.sub.0] or [S.sub.0] to [A.sub.0]), (8) is used.

6. Results and Discussion

6.1. Model: [[0].sub.4] without Defect. The [A.sub.0] mode was excited from the left edge of the plate by concentrated force at the actuator C (see Figure 4). The [A.sub.0] Lamb wave is the focus in this study because of its sensitivity to the small defects. To verify the excitability of pure mode [A.sub.0], 2D-FFT was performed at the sensor A. A matrix was calculated at uniformly spaced points.

Figure 5 shows that there is only one mode propagating which is [A.sub.0].

6.2. Model: Symmetric Delamination 60 x 0.1. Figure 6 is the delaminated model. Figure 7 is a snapshot of FE out-of plane displacement. The Lamb waves split into two parts and travel independently with different velocities in the upper and the lower sublaminates. Mode conversions happen at the two edges of a delamination due to the change of boundary conditions. To characterize the delamination, we analysed the signals picked up at the sensors A and B.

6.3. Modes Conversion. In Figure 8, the first wave group is a forward traveling wave group, which is an excited [A.sub.0] mode at x =0. When this interacted with the entrance of the delamination, there was a low amplitude reflected wave group. This reflected wave group appears as the second wave group [A.sub.0][A.sub.0]. Delamination separates the plate into two sublaminates: upper and lower. The transmitted wave converted to the symmetric and antisymmetric mode [A.sub.0][S.sub.0] and [A.sub.0][A.sub.0] which traveled within the sublaminates with different velocities. The first wave [A.sub.0][S.sub.0U]--U, L mean that the mode travel, respectively, in the upper and lower sublaminate--reached first the exit of delamination; this is justified by the fact that symmetric mode is faster than the antisymmetric mode. The backward mode [A.sub.0][S.sub.0U][S.sub.0U] passes through the upper and then is transmitted to the main laminate as the second wave group [A.sub.0][S.sub.0U][S.sub.0U][A.sub.0]. By the same manner, in the lower sublaminate the mode [A.sub.0][S.sub.0L][S.sub.0L] is transmitted to the main laminate as [A.sub.0][S.sub.0L][S.sub.0L][A.sub.0]. In the case of symmetric delamination the two modes [A.sub.0][S.sub.0U][S.sub.0U][A.sub.0] and [A.sub.0][S.sub.0L][S.sub.0L][A.sub.0] are reflected at the same time.

6.4. Results: Sensor A. Figure 9 is A-scan image from the numerical simulations, taken at 100 mm for a delamination length of 60 mm. As explained in Figure 8, we conclude that the first arrived wave is the incident mode [A.sub.0] and the second is the first reflected wave [A.sub.0][A.sub.0]. The delamination is symmetric so two waves arrived at the same time as one packet which is [A.sub.0][S.sub.0U][S.sub.0U][A.sub.0] + [A.sub.0][S.sub.0L][S.sub.0L][A.sub.0].

Based on the 2D-FFT computed using Matlab program applied to the surface of delaminated skin (before the delamination), Figure 10 shows that the incident and the reflected modes are antisymmetric which confirms that the first reflected mode is [A.sub.0][A.sub.0].

6.5. Characterization of Delamination from Data Acquired at Sensor A. Figure 11 presents wavelet coefficients versus time at sensor A. The time delay between the peaks permits estimating the position and the length of delamination.

Knowing the group velocity of the modes [A.sub.0] and [S.sub.0]: Vg ([A.sub.0],300kHz)=1268 m/s, Vg ([S.sub.0],300kHz)=5649 m/s, we can calculate the delamination position from the sensor A noted [P.sub.D] by [DELTA][t.sub.1] (Delta 1) and delamination length noted [L.sub.D] by [DELTA][t.sub.2] (Delta 2) as presented in Table 2.

The sensor A permits evaluating the position and the length of symmetric and asymmetric delamination. The errors associated with the predicted symmetric delamination position range from 3.1% to 6.6%. However in the case of asymmetric delamination, the error is less than 3.8%. As far as the length prediction is concerned, the errors range from 3.6% to 6.9% in symmetric delamination and from 2.9% to 5.9% in asymmetric delamination. So we conclude that the longer the delamination, the higher the estimation.

6.6. Results: Sensor B. Figure 12 represents different wave modes in the case where [A.sub.0] mode is incident on the transmission side of the main laminate at sensor B.

This figure represents different wave modes in the case where [A.sub.0] mode is incident on the transmission side of the main laminate at sensor B. A new mode [S.sub.0] was generated when the [A.sub.0] interacted with the entrance of delamination as shown in Figure 8. This new mode traveled within the upper sublaminates along the length of delamination. Then it reached the exit of delamination, interacted with the exit, and generated a new mode [A.sub.0] in the forward direction. This new mode propagated in the main laminate, called the [A.sub.0][S.sub.0U][A.sub.0] mode. In the lower sublaminate the mode is called [A.sub.0][S.sub.0L][A.sub.0]. Two modes arrived at the same time in the case of symmetric delamination.

6.7. Characterization of Delamination from Data Acquired at Sensor B. Figure 13 presents wavelet coefficients versus time at sensor B. The [DELTA][t.sub.1] is the time delay between two transmitted symmetric modes. The [DELTA][t.sub.2] is the time delay between the first transmitted symmetric mode and the third antisymmetric mode, so knowing the group velocity of the mode [S.sub.0]: Vg ([S.sub.0], 300 kHz) =5649 m/s, we can calculate the delamination length noted [L.sub.D1] by (7) and [L.sub.D2] by (8). Table 3 resumes the results found.

The sensor B permits evaluating only the length of symmetric and asymmetric delamination. The errors associated with the predicted symmetric delamination length range from 1.2% to 4.9%. In the case of asymmetric delamination the errors range from 3.5% to 5.9%. So we conclude that the longer the delamination, the higher the estimation. Also, the sensor B gives accurate estimation in case of symmetric delamination.

7. Experimental Verification

We validate our model based on Barra results [23]; the author studied by FEM the [A.sub.0] Lamb mode interaction with delamination in sandwich skin. Based on Fourier Diamond [26, 27], he has estimated the delamination length. The obtained results are validated by experimental study. These studies have been done by the propagation of Lamb waves on air by using a Laser Doppler velocimetry.

To validate our model and our method we followed the same methodology, as presented in Figure 14.

The S(x, t) is the measured time-displacement matrix at the skin surface. IFFT is the Inverse Fast Fourier Transform.

7.1. Model: Delamination 24 x 0.1. The B-scan illustrated in Figure 16 represents the S(x, t): time-displacements matrix picked up at the surface of limited zone (see Figure 15).

Figure 16(a) indicates all the interactions of [A.sub.0] Lamb mode with delamination in the skin. Figure 16(b) is the temporal evolution of out-of-plane displacement on the upper surface at x= 185 mm (blue line). To evaluate the defect length, and following the Diamond method, we have first of all separated the incident and the reflected waves. Then the separated incident waves get filtered to remove the undesirable reflections.

Figure 17 shows the filtered incident waves. We can easily see the mode perturbation in the studied zone. This is due to the delamination presence. To evaluate the defect length we computed the temporal FFT to the filtered signal as presented in Figure 18.

Figure 18 shows the principal lobe localized at the frequency 300 kHz which verifies the excitation frequency. To measure the delamination length, a cut of the temporal FFT at the frequency 300 kHz must be done to show clearly the peaks of the lobes.

Figure 19 permits measuring the delamination length. We measure it between the peaks of the lobes. The delamination length is 22 mm.

To conclude, the model gives an accurate result with an error of 8.3%. The errors are due to the approximated numerical model.

8. Conclusions

In this work, we have studied the numerical model describing the propagation of antisymmetric mode [A.sub.0] within a sandwich skin. Simulations based on finite element method were carried out using ABAQUS software in order to investigate the interaction of Lamb wave mode by symmetric and asymmetric through-thickness delamination. The results showed the conversion phenomenon. To quantify the conversion and to characterize the delamination, we have computed the 2D-FFT in order to identify the propagating and the converted modes; after that, the WT was calculated at sensors A and B to measure the arrival times.

Table 4 compared the delamination length calculated at the two sensors A and B. It shows that sensor A gives more accurate estimation than sensor B. Moreover, sensor A permits also estimating the start of the delamination. So the optimal position to evaluate the position and the length of delamination is between the actuator and the defect.

Moreover, comparing the signals obtained at two sensors: A and B, it was found that the mode conversions happen at the edges of a delamination for [A.sub.0] wave. In fact, this mode is sensitive to the position and to the length of delamination; this makes it an effective tool to evaluate the delamination in orthotropic materiel. Besides, based on signal changes with the delamination edges, a localization method is proposed to estimate the position and the length of the delamination. The proposed method was validated based on previous experimental work.

These are the main results:

(i) The estimation is accurate when the delamination length increases.

(ii) The optimal position to evaluate the beginning and the length of delamination is between the actuator and the defect which corresponds to the pulse-echo method.

As perspective, we model the whole sandwich structure and we characterize the defect by reflection and transmission coefficients.

Data Availability

The data used to support the findings of this study are available from the corresponding author upon request.

Conflicts of Interest

The authors declare that there are no conflicts of interest regarding the publication of this paper.


The research and publication of this article were funded by FST, Settat. The authors would like to express their gratitude to Elhadji Barra Ndiaye, Ph.D., for his help in the model verification.


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Salah Nissabouri (ID), (1) Mhammed El allami, (1,2) El Hassan Boutyour, (1) and Ahmed Errkik (1)

(1) LMEET Lab, Department of Applied Physics, FST, Settat 26000, Morocco

(2) CRMEF, Settat, Morocco

Correspondence should be addressed to Salah Nissabouri;

Received 15 June 2018; Revised 13 October 2018; Accepted 12 November 2018; Published 28 November 2018

Academic Editor: Kim M. Liew

Caption: Figure 1: Sandwich structure with delaminated skin.

Caption: Figure 2: Dispersion curves (wavenumber versus frequency).

Caption: Figure 3: Excitation windowed by Hann window.

Caption: Figure 4: Numerical model without defect, C: actuator, A and B: sensors.

Caption: Figure 5: Superposition of 2D-FFT over analytical dispersion curves.

Caption: Figure 6: Numerical model of symmetric delamination.

Caption: Figure 7: Snapshot of FE simulated out-of plane displacement in the upper and the lower sublaminates separated by the delamination.

Caption: Figure 8: [A.sub.0] reflection at the entrance and at the end of asymmetric delamination (length 60), case [A.sub.0] incident; R denotes reflected mode and T denotes transmitted mode.

Caption: Figure 9: Out-of-plane displacement, taken on damaged composite [[0].sub.4] at x = 100 mm, case symmetric delamination length 60.

Caption: Figure 10: Superposition of 2D-FFT applied before the delamination over analytical dispersion curves.

Caption: Figure 11: Coefficients of wavelet gaus1, case [A.sub.0] incident, delamination length 60, between layer 2 and layer 3.

Caption: Figure 12: Out-of-plane displacement, taken on damaged composite [[0].sub.4] at x = 300 mm, case symmetric delamination length 60.

Caption: Figure 13: Coefficients of wavelet gaus1, case symmetric delamination length 60.

Caption: Figure 14: Fourier Diamond.

Caption: Figure 15: Model geometry.

Caption: Figure 16: (a) Wavefields of [A.sub.0] mode interaction with delamination. (b) Cut of S(x, t) at the position 185 mm.

Caption: Figure 17: Filtered wavefields of incident waves.

Caption: Figure 18: S(x, f) temporal FFT applied to the filtered incident waves.

Caption: Figure 19: Cut of S(x, f) at the frequency 300 kHz.
Table 1: Elastic coefficients [C.sub.ij] and density [rho]
of the materiel.

[rho]               [C.sub.11](GPa)     [C.sub.22] = [C.sub.33]

1530                     56,9                     14,7

[rho]               [C.sub.12] = [C.sub.13]
(kg/[m.sup.3])            = [C.sub.23]

1530                          9,76

[rho]               [C.sub.55] = [C.sub.66]

1530                          4,16

Table 2: Delamination localisation from data acquired at sensor A.

Delamination     Length   [P.sub.D]    [P.sub.DTH]    Error %

1 and 2            60       103,8          100          3,8
                   90       103,9          100          3,9
                  120       103,8          100          3,8

2 and 3            60       103,2          100          3,2
                   90       106,6          100          6,6
                  120       103,1          100          3,1

Delamination     Length   [L.sub.D]    Error %

1 and 2            60        62,0        3,3
                   90        93,3        3,7
                  120       123,4        2,9

2 and 3            60        62,2        3,7
                   90        94,1        4,5
                  120       120,9        0,8

Table 3: Delamination localisation from data acquired at sensor B.

Delamination     Length   [L.sub.D1]    Error %    [L.sub.D2]

1 and 2            60        49,1         18,1        62,1
                   90        93,5         3,9         95,2
                  120        127,1        5,9         127,7

2 and 3            60        45,5         24,2        62,9
                   90        98,9         9,8         94,0
                  120        121,5        1,2         122,5

Delamination     Length   Error %    Min Error %

1 and 2            60       3,5          3,5
                   90       5,7          3,9
                  120       6,4          5,9

2 and 3            60       4,9          4,9
                   90       4,5          4,5
                  120       2,1          1,2

Table 4: Comparison between results at sensors A and B.

Delamination                   Sensor A
Position         Length
                          [L.sub.D]    Error %

1 and 2            60        62,0        3,3
                   90        93,3        3,7
                  120       123,4        2,9

2 and 3            60        62,2        3,7
                   90        94,1        4,5
                  120       120,9        0,8

3 and 4            60        62,0        3,3
                   90        93,3        3,7
                  120       123,4        2,9

Delamination                    Sensor B
Position         Length
                          [L.sub.D]    Error %

1 and 2            60        62,1        3,5
                   90        93,5        3,9
                  120       127,1        5,9

2 and 3            60        62,9        4,9
                   90        94,0        4,5
                  120       121,5        1,2

3 and 4            60        62,1        3,5
                   90        93,5        3,9
                  120       127,1        5,9
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Title Annotation:Research Article
Author:Nissabouri, Salah; El allami, Mhammed; Boutyour, El Hassan; Errkik, Ahmed
Publication:Advances in Acoustics and Vibration
Article Type:Report
Date:Jan 1, 2018
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