Document Type: Research Paper
Authors
^{1} Department of Mechanical Engineering, University of Kashan, Kashan, 8731751167, Iran
^{2} Department of Mechanical Engineering, Faculty of Engineering, University of Isfahan, Isfahan, 8174673441, Iran
Abstract
Keywords
Modal Characteristics of Composite Beams with Single Delamination A Simple Analytical Technique
K. Torabi^{a}, M. ShariatiNia^{a*}, M. HeidariRarani^{b}
^{a }Department of Mechanical Engineering, University of Kashan, Kashan, 8731751167, Iran
^{b}Department of Mechanical Engineering, Faculty of Engineering, University of Isfahan, Isfahan, 8174673441, Iran
paper INFO 

ABSTRACT 
Paper history: Received 9 August 2014 Received in revised form 14 October 2014 Accepted 27 October 2014 
In the present research, the effects of delamination size and location on vibration characteristics of laminated composite beams are investigated both analytically and numerically. In the analytical method, the delaminated beam is modeled as four interconnected Euler–Bernoulli beams and the constrained and free mode models are both simulated. The differential stretching and the bendingextension coupling are considered in the formulation. Analytical expressions for displacement functions are presented in a simple form based on the basic standard trigonometric and hyperbolic functions. This new technique considerably simplifies the calculations regardless of the number of delaminations. In finite element method, delaminated composite beams are modeled in commercial finite element software, ABAQUS, and natural frequencies and mode shapes are extracted from the modal analysis. Analytical results are compared with finite element ones and available experiments in the literature. Finally, the generated database for different sizes and locations of delamination can be used to detect the existence of delamination in laminated composite beams and thento specify the size and location of delamination. 



Keywords: Composite beams Delamination detection Vibration analysis Basic functions Finite element method (FEM)



© 2014 Published by Semnan University Press. All rights reserved. 
1. Introduction
Advanced composite materials are increasingly used in structural designs of aircraft, helicopters, spacecraft, automobiles, marine and submarine vehicles because of the desirable properties such as high strength and stiffness, lightweight, fatigue resistance, and damage tolerance, etc. However, composites are very sensitive to the anomalies induced during their fabrication or service life. One of the commonly encountered types of defects or damage in laminated composite structures is delamination. Delaminations may originate during fabrication or may be serviceinduced, such as by impact or fatigue loading. Delaminations not only affect the strength and integrity of the structure but also cause the reduction in the stiffness, thus affecting its vibration and stability characteristics. Reflections of these effects in dynamic response are the alteration of natural frequencies and damping ratios. As a result, considerable analytical, numerical and experimental efforts have been expended to capture these phenomena.
One of the earliest models for vibration analysis of composite beams including delaminations was proposed by Ramkumar et al. [1]. They modeled a beam with one throughthickness delamination simply using four Timoshenko beams connected at delamination edges. Natural frequencies and mode shapes were solved by a boundary eigenvalue problem. Using this model, the predicted natural frequencies were consistently lower than the results reported in experimental measurements. Authors attributed this discrepancy to the effect of contact with the delaminated "free" surfaces during vibrations. They suggest that the inclusion of the contact effect may improve the analytical prediction.
To study the effect of a throughthickness delamination on the free vibration of an isotropic beam, Wang et al. [2] present an analytical model using four EulerBernoulli beams that are joined together. They assum that the delaminated layers deform "freely" without touching each other ("free mode" model) and will have different transverse deformations.
Later, Mujumdar and Suryanarayan [3] presented two models namely the free mode model and the constrained mode model for the flexural vibrations of isotropic beams with delamination at the midplane as well as at the offmidplane locations. Experimental results have also been presented for various cases of delaminations in the beams. This paper concludes that the constrained mode model in which the transverse displacement and the normal stress of the upper and lower layer at the delaminated interface have been constrained to be the same, gives results in good agreement with the experimental results. The free mode model (similar to the one developed by Wang [2]) underestimates the frequencies, particularly at the higher modes.
The "constrained model" fails to explain the delamination opening modes found in experiments [4]. In these experiments conducted by Shen and Grady, the opening modes were even found in the first bending mode of the beam for some delamination cases. However, their finite element formulations (Model A and B) were essentially followed by the "constrained model" by Mujumdar and Suryanarayan [3] and the "free model" by Wang et al. [2]. In this paper the "Model A" is corresponding to the "constrained model" and the "Model B" is corresponding to the "free model". The discrepancy between the results predicted by the two models is significant even in cases where mode shapes do not show any opening in the delamination region. Furthermore, in some cases, opening delamination modes are shown clearly in their experiment, while the "constrained model" frequency prediction has a better match with the corresponding experimental results for these modes, even though the delamination cannot open using the "constrained model".
An analytical model based on the Timoshenko beam theory is presented by Hu and Hwu [5] for the free vibrations of delaminated sandwich beams. The natural frequencies and the mode shapes of the delaminated composite sandwich beams are presented in this paper. Lee [6] presents a displacementbased layerwise finite element model for the analysis of free vibration of delaminated beam. In which the effects of the fiber angle, location, size and number of delamination are investigated numerically. A review paper on the vibrationbased modeldependent damage (delamination) identification and health monitoring for composite structures is presented by Zou et al. [7]. This paper deals with various models proposed for the free vibrations of delaminated beams.
In the analytical research done by Luo and Hanagud [8], a piecewiselinear spring model is used to simulate the behavior between delaminated surfaces. Shear and rotary inertia effects, as well as bendingextension coupling, are included in the governing equations. Frequencies and mode shapes are solved through a boundary eigenvalue problem. The proposed model includes the "free model" and the "constrained model" as special cases. The nonlinear response simulated by this model shows good agreement with the experiment results.
Karmakar et al. [9] studied the effect of delamination on free vibration characteristics of graphiteepoxy composite pretwisted shallow shells of various stacking sequences considering length of delamination as a parameter. An exhaustive review on the vibration of delaminated composites has been presented by Della et al. [10]. The paper deals with various analytical models and numerical analysis for the free vibration of composite laminates. Della et al. [11] develop analytical solutions to study the free vibrations of multiple delaminated beams under axial compressive loadings. The Euler–Bernoulli beam theory and free mode and constrained mode assumptions in delamination buckling and vibration are used in the analysis. Ramtekkar [12] presented free vibration analysis of laminated beams with delamination using mixed finite element model. Analytical solutions for beams with multiple delaminations were presented by some researchers. Shu and Della [13, 14] and Della and Shu [15] used the "free mode" and "constrained mode" assumptions to study a composite beam with various multiple delamination configurations. Their study emphasized the influence of a second delamination on the first and second natural frequencies and the corresponding mode shapes of a delaminated beam. Shariati Nia et al. [16] presented an analytical method for calculating natural frequencies of a delaminated composite beam from both free and constrained mode frequencies. An improved combined natural frequency is proposed in this new formulation based on the breathing of delamination.
In this paper, at first, the delaminated beam is modeled as four interconnected EulerBernoulli beams. The free mode and constrained mode models are considered. Furthermore, the expressions for displacement functions are presented in a more convenient form based on concerning basic standard trigonometric and hyperbolic functions. The proposed technique considerably simplifies the calculation, and regardless of the number of delaminations, the problem can be solved by a 2×2 system of equations. Also, delaminated composite beams with different sizes and locations of delaminations are modeled in commercial finite element software, ABAQUS, and natural frequencies are extracted from the modal analysis.
2. Analytical Modelling of a Delaminated Composite Beam
Fig 1.(a) shows a cantilever beam with a single delamination at an arbitrary location and various lengths. L, h and a are beam length, beam thickness and delamination length, respectively.
(a) 
(b) 
Figure 1. a) Geometry of the delaminated beam, b) Model of delaminated beam with four interconnected beams 
The beam is separated along the interface by a delamination with length a located at the centre of the beam. The beam can be subdivided into three spanwise regions, a delamination region and two integral regions. The delamination region is comprised of two segments (delaminated layers), beam 2 and beam 3, which are joined at their ends to the integral segments, beam 1 and beam 4. Each of the four beams is treated as beams with different boundary conditions.
2.1. Free Mode Model
In "free mode" model, it is assumed that the delaminated layers deform "freely" without touching each other and have different transverse deformations. The governing equations for the free vibration of a delaminated beam using the Euler–Bernoulli beam theory are as the following:
(1) 
where D_{i} is the equivalent bending stiffness of the ith beam, m_{i} is the mass per unit length and is equal to , ρ_{i} is the mass density and A_{i} is the crosssectional area of the beam. The bending stiffness for homogeneous and isotropic beams is given by D_{i}=EI_{i}, where E denotes the Young’s modulus and I is the moment of inertia. The mechanical properties of the composite beams are determined using the classical lamination theory (CLT) as follows:
(2) 
where is the extensional stiffness, is the bendingextension coupling stiffness, and is the bending stiffness of the ith beam [13].
For free vibration, the solution of Eq. (1) is given as follows:
(3) 
where ω is the natural frequency and W_{i} is the mode shape. Substituting Eq. (3) for Eq. (1) and eliminating the trivial solution sin(ωt)=0, one can obtain the general solutions of the differential equation in Eq. (1) as follows:
(4) 
where,
(5) 
and λ_{i} are the nondimensional frequencies. The lowest eigenvalue λ is the nondimensional primary frequency of the beam. The 16 unknown coefficients C_{i}, S_{i}, CH_{i} and SH_{i} are determined by four boundary conditions and twelve continuity conditions.
For cantilever beam B.C.'s at fixed end are as follows:
(61) 
=0 , 
and at free end (x=L)
(62) 
=0 , 
Continuity conditions at x=x_{1}
(71) 

(72) 

(73) 

(74) 
(x=0)
where,
(8) 
The second term on the left side of Eqs. (74) represents the contribution to the bending moment from the differential stretching between beams 2 and 3 and contributes to the bending stiffness of the beam [3, 1315]. Similarly, the continuity conditions at the end tip of delamination (x=x_{2}) are derived. The boundary conditions and continuity conditions provide 16 homogeneous equations for 16 unknown coefficients. A nontrivial solution for the coefficients exists only when the determinant of the coefficient matrix vanishes. The frequencies and mode shapes can be obtained as eigenvalues and eigenvectors, respectively.
2.2. Constrained Mode Model
The "constrained mode" model is simplified by the assumption that the delaminated layers are in touch along their whole length all the time, but are allowed to slide over each other. Therefore, the delaminated layers have the same transverse deformations (w_{3}=w_{2}). This is reasonable since if there is no opening in the delamination region, the "free model" and "constrained model" are essentially the same. In this model the governing equations are as the following:
(91) 
For beams 2 and 3
(92) 
where,
(101) 
D_{23}=D_{2} + D_{3} 
(102) 
m_{23}=m_{2} + m_{3} 
The generalized solutions for the constrained model are identical in form to the free model. The unknown coefficients C_{i}, S_{i}, CH_{i} and SH_{i}, however, are reduced to twelve coefficients which can be determined by four boundary conditions and eight continuity conditions.
B.C.'s for cantilever beam at fixed end (x=0) and free end (x=L) are the same as Eqs. (61) and (62), but four continuity conditions at x=x_{1} are as follows:
(111) 

(112) 

(113) 

(114) 
Similarly, four continuity conditions at the end tip of delamination (x=x_{2}) can be derived. These boundary and continuity conditions provide 16 homogeneous equations for 16 unknown coefficients.
According to these procedures, the characteristic equation of a beam with one delamination relies on the solution of a determinant of order 16 for free mode model and 12 for constrained mode model. Furthermore, this determinant order increases by varying the number of delamination and converting single delamination to multiple delaminations. This method is computationally expensive to analyze the presence of multiple delaminations in beams.
2.3. Basic Functions
The expressions for the displacements of beams as general solution of the differential equations in Eq. (9) can be written in a simple form based on the basic standard trigonometric and hyperbolic functions and in terms of just four factors: the displacement W_{0}, slop , bending moment M_{0}, and shear force V_{0} at x=0.
(12) 
where the functions of g_{i}(x) are expressed as follows:
(131) 

(132) 

(133) 

(134) 
2.3.1. Constrained Mode Model
According to basic functions expressed in Eq. (13) and the boundary conditions at fixed end of beam 1, transverse deformations of beam 1 can be written as follows:
(14) 
Based on two continuity conditions at x=x_{1} for displacement and slope, and according to Eqs. (111) and (112), deflection of beam 2 is as follows:
(15) 
These unknown coefficients ( ) can be obtained using two other continuity conditions at x=x_{1} for bending moment and shear force, which are expressed in Eq. (113) and (114) as follows:
(161) 

(162) 
Similarly, based on two continuity conditions at x=x_{2} for displacement and slope, deflection of beam 4 is as the following:
(17) 
Also, these unknown coefficients can be obtained from two other continuity conditions at x=x_{2} for bending moment and shear force as follows:
(181) 

(182) 
Finally, the other two unknown coefficients (M_{0}, V_{0}), are obtained by using two equations from boundary conditions at free end of beam 4. Natural frequencies and mode shapes can be obtained by solving this simple system of equations.
The general solution proposed in this method satisfies the compatibility conditions at the delamination tips, and two of the factors are obtained directly from the type of support at x=0. The other two factors are obtained by the system of two equations from the boundary conditions at x=L. The technique used considerably simplifies the calculation, and regardless of the number of delaminations, the problem can be solved by a 2×2 system of equations.
2.4. Numerical Investigations
Numerical investigations are undertaken for the free vibrations of crossply laminated beams with embedded internal delaminations of different sizes and at several different locations. For this purpose, an eightlayer symmetric crossply laminated [0/90]_{2s} beam, under the clampedfree supports is considered. Thickness direction delamination locations are defined as mentioned in work of Shen and Grady [4]. "Interface 1" implies the midplane delamination, while "Interface 4" implies the skin ply delamination and so on. Lengthwise delamination locations are at the middle of beams. Fig. 2 shows interfaces and dimensions for a crossply delaminated beam.
Figure 2. Geometry of the eight layer symmetric composite laminated beam [0/90]_{2s} (Various interfaces for delamination) 
3. Finite Element Modelling
The delamination is introduced as a debonding of adjoining plies in the laminated composite beam. The geometry of the delaminated beam is shown in Fig 1. The finite element modelling for simulating the delaminated beams and extracting the natural frequencies is conducted using the commercial finite element software ABAQUS. The composite beam is modeled as a cantilever with length (L) 127 mm, width (b) 12.7 mm and total thickness (h) 1.016 mm with delamination of length of 25.4, 50.8, 76.2, and 101.6 mm along one of the four ply interfaces shown in Fig 2. Nominal thickness of each ply is 0.127 mm and delamination dimensionless length (a/L) is 0.2, 0.4, 0.6, and 0.8. Material properties of unidirectional composite ply are presented in Table 1.
Table 1. Mechanical properties of the laminated beam 

E_{11} (GPa) 
E_{22} (GPa) 
G_{12 }(GPa) 
υ_{12} 
ρ (kg/m^{3}) 

134.49 
10.34 
5.00 
0.33 
1500 

A shell element formulation is adopted since the beam is comparatively thin (h/b is less than 10 and h/L is less than 100). The composite laminates are modeled using a double layer of shells, with reduced integration and three integration points over the thickness (ABAQUS element type S4R, Simpson’s rule for shell section integration), and an orthotropic material definition is used. Modelling a delamination generally involves nonlinearities, due to the opening and closing of the delamination during cyclic deformation of the structure and friction between the two faces of the delamination. This requires explicit solvers and timedomain simulations.
At "free mode" model, there is no interaction defined between the surfaces of the delamination. Consequently, the elements on either side of the delamination deform freely and can separate and penetrate each other, effectively, causing a lower stiffness and absence of damping induced by contact during cyclic closing of the delamination. At "constrained mode" model, standard surfacetosurface contact interactions with normal and tangential behavior are introduced between the surfaces of the two sublaminates, which allow neither penetration nor separation between the sublaminate structures. Therefore, the delaminated layers have the same transverse deformations. Based on the model proposed and material properties, a total of 33 cases including an intact beam and 32 delaminated beams with different delamination lengths and different delamination interfaces are calculated. Natural frequencies are compared with the experimental results provided in Ref. [4].
4. Results and Discussion
The fundamental frequencies of a delaminated composite beam with various locations and sizes of delamination are presented in Tables 25. The experimental and analytical results related to model A (constrained model) and model B (free model) are provided from Ref. [4]. It is observed that the fundamental frequencies obtained from analytical and finite element method, closely match the experimental results of Ref. [4] for most of the cases.
Table 2. Fundamental natural frequency (Hz), Interface 1 



Shen and Grady [4] 

Present Study 



Exp 
Analytical 

FEM 
Analytical 


Const 
Free 

Const 
Free 
Const^{a} 
Const^{b} 

0.0 
79.83 
82.04 
82.04 

82.12 
82.12 
82.21 
82.21 


0.2 
78.17 
80.13 
67.36 

80.17 
68.67 
80.63 
80.41 


0.4 
75.37 
75.29 
56.48 

75.60 
58.09 
76.10 
75.27 


0.6 
67.96 
66.94 
47.90 

66.64 
48.97 
68.04 
66.4 


0.8 
57.54 
57.24 
40.59 

56.18 
41.16 
58.47 
56.23 


^{a} Without bendingextension coupling. ^{b} With bendingextension coupling. 


Table 3. Fundamental natural frequency (Hz), Interface 2
^{a} Without bendingextension coupling. ^{b} With bendingextension coupling.
Table 4. Fundamental natural frequency (Hz), Interface 3
^{a} Without bendingextension coupling. ^{b} With bendingextension coupling.
Table 5. Fundamental natural frequency (Hz), Interface 4
^{a} Without bendingextension coupling. ^{b} With bendingextension coupling. 
Comparing constrained mode and free mode model, for delaminations located near the beam surfaces, free mode models have better agreement with experimental results. Figures 3 and 4 show the first three mode shapes for constrained and free mode models respectively. Delamination dimensionless length (a/L) is 0.4 and is located along interface 4. Blue elements show points with no deflection and refer to nodes of mode shapes. Furthermore, the second and third frequencies obtained from finite element analysis and analytical results from basic function formulation are presented in Tables 69. Comparing constrained mode and free mode model, and according to first three mode shapes, when delamination locates on the node of one mode shapes, the discrepancy decreases between related free mode and constrained mode frequencies.
(a) 

(b) 

(c) 

Figure 3. First three mode shapes of delaminated beam (Interface 4 and a/L=0.4) for constrained mode model a) 1^{st} mode, b) 2^{nd} mode shape, c) 3^{rd} mode


(a) 

(b) 

(c)

Table 6. 2^{nd} and 3^{rd} natural frequencies (Hz) for analytical delamination along interface 1.

2^{nd} mode 

3^{rd} mode 

FEM 
Analytical 

FEM 
Analytical 

Const 
Free 
Const^{a} 
Const^{b} 

Const 
Free 
Const^{a} 
Const^{b} 

0.0 
514.02 
514.02 
515.26 
515.26 

1437.00 
1437.00 
1449.89 
1449.89 
0.2 
488.99 
348.73 
490.31 
487.13 

1216.50 
1217.40 
1257.99 
1233.16 
0.4 
485.28 
313.94 
462.55 
455.82 

851.87 
852.73 
909.21 
872.53 
0.6 
426.48 
284.14 
406.94 
395.30 

752.00 
746.88 
802.87 
770.64 
0.8 
332.95 
248.31 
332.18 
318.28 

720.38 
677.55 
768.85 
734.03 
^{a} Without bendingextension coupling.
^{b} With bendingextension coupling.
Table 7. 2^{nd} and 3^{rd} natural frequencies (Hz) for delamination along interface 2.

2^{nd} mode 

3^{rd} mode 

FEM 
Analytical 

FEM 
Analytical 

Const 
Free 
Const^{a} 
Const^{b} 

Const 
Free 
Const^{a} 
Const^{b} 

0.0 
514.02 
514.02 
515.26 
515.26 

1437.00 
1437.00 
1449.89 
1449.89 
0.2 
480.65 
342.71 
495.00 
489.24 

1229.50 
1231.30 
1289.91 
1251.77 
0.4 
481.85 
310.50 
472.02 
460.49 

870.19 
871.55 
963.05 
899.63 
0.6 
431.19 
284.06 
423.33 
403.69 

767.48 
763.55 
851.24 
794.39 
0.8 
341.09 
250.47 
352.41 
328.43 

735.51 
693.55 
820.74 
759.63 
^{a} Without bendingextension coupling.
^{b} With bendingextension coupling.
Table 8. 2^{nd} and 3^{rd} natural frequencies (Hz) for delamination along interface 3.

2^{nd} mode 

3^{rd} mode 

FEM 
Analytical 

FEM 
Analytical 

Const 
Free 
Const^{a} 
Const^{b} 

Const 
Free 
Const^{a} 
Const^{b} 

0.0 
514.02 
514.02 
515.26 
515.26 

1437.00 
1437.00 
1449.89 
1449.89 
0.2 
493.59 
441.50 
504.98 
504.13 

1372.40 
1374.50 
1383.79 
1382.04 
0.4 
497.61 
378.81 
494.66 
493.25 

1172.10 
1102.00 
1191.86 
1186.15 
0.6 
483.71 
451.89 
472.89 
470.99 

1064.00 
1156.40 
1083.32 
1076.74 
0.8 
438.10 
423.84 
430.14 
427.71 

1043.10 
1060.30 
1061.96 
1055.06 
^{a} Without bendingextension coupling.
^{b} With bendingextension coupling.
Table 9. 2^{nd} and 3^{rd} natural frequencies (Hz) for delamination along interface 4.

2^{nd} mode 

3^{rd} mode 

FEM 
Analytical 

FEM 
Analytical 

Const 
Free 
Const^{a} 
Const^{b} 

Const 
Free 
Const^{a} 
Const^{b} 

0.0 
514.02 
514.02 
515.26 
515.26 

1437.00 
1437.00 
1449.89 
1449.89 
0.2 
490.79 
465.59 
508.85 
505.69 

1377.90 
1381.60 
1397.59 
1392.17 
0.4 
495.86 
413.08 
501.64 
496.41 

1192.80 
1152.30 
1239.71 
1220.29 
0.6 
485.50 
451.20 
484.34 
477.50 

1088.90 
1141.50 
1140.50 
1116.76 
0.8 
444.67 
423.11 
447.88 
439.25 

1069.00 
1078.70 
1121.30 
1096.38 
^{a} Without bendingextension coupling.
^{b} With bendingextension coupling.
Also, analytical frequencies of delaminated beam with bendingextension coupling assumptions decrease more rather than without bendingextension coupling condition.
Here, first three natural frequencies are presented for single delamination located at various lengthwise locations. Tables 10 and 11 show results for beams with clampedfree and clampedclamped boundary conditions respectively. Delamination length (a/L) is 0.2 and is located in interface 1 (midplane) through thickness for all cases.
Natural frequencies from constrained mode model of finite element analysis better match the experiments, for all cases. Also for small delamination lengths (a/L<0.3) there is no considerable difference between analytical frequencies obtained from both constrained and free mode model, especially for lower natural frequencies. Therefore, only results of constrained mode model with bendingextension coupling are presented here.
5. Conclusion
In this study, a new simple mathematical technique is proposed for free vibration analysis of a delaminated composite beam with any numbers of delaminations. This technique is verified for a composite beam with single delamination. Therefore, a delaminated beam is divided into four EulerBernoulli beams and beams on both sides of delamination have free or constrained modes. The effects of delamination size and location on vibration characteristics of laminated composite beams are investigated. Modal parameters are extracted using both analytical and finite element methods. In the analytical part, the expressions for displacement functions are written based on basic standard trigonometric and hyperbolic functions for simplifying the calculation. In the finite element part, constrained mode and free mode models are simulated using suitable elements, boundary conditions, interactions and constrains. The numerical results are validated by the analytical and experimental results available in the literature for some case studies. These results of the proposed analytical method and finite element method show good agreement with them and with each other.
Table 10. First three natural frequencies (HZ) for Clampedfree boundary conditions
Table 11. First three natural frequencies (HZ) for Clampedclamped boundary conditions

The numerical results show that delamination in composite beams affects the natural frequencies and this change depends not only on the size of delamination but also on its location. Comparing constrained mode and free mode model, the natural frequencies obtained from free mode model are comparatively lower than the results of constrained mode model. This discrepancy can be attributed to the effect of contact between the delaminated surfaces during vibrations. Also, for delaminations located near the beam surfaces, free mode models have better agreement with them and with experimental results. Vice versa, when delamination moves from the surface to the midplane of beam, constrained mode frequencies better match the experiment. Also according to corresponding mode shapes, when delamination locates on the node of one mode shapes, the discrepancy decreases between related free mode and constrained mode frequencies.
Natural frequencies from constrained mode model of finite element analysis better match the experiment, for all cases. Also, for small delamination lengths (a/L<0.3) there is no considerable difference between analytical frequencies obtained from both constrained and free mode model, especially for lower natural frequencies.
Finally, the obtained results can be used as a database to predict the frequency behaviour of a delaminated beam by changing the size and location of delamination. The results show that if the effect of the delamination can be accurately predicted, then changes in modal parameters can be used to determine the location and extent of delamination in composite structure.
Nomenclature
L 
beam length 
h 
beam thickness 
b 
beam width 
A 
delamination length 
D 
reduced bending stiffness 
ρ 
mass density 
A 
crosssectional area 
extensional stiffness 

coupling stiffness 

bending stiffness


ω 
natural frequency 
W 
mode shape 
λ 
nondimensional frequency 
Acknowledgements
The authors are grateful to the University of Kashan for supporting this work by Grant No. 363463/1.
References
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* Corresponding author. Tel.: +983155912448; Fax: +983155511121
Email address: m.shariati@grad.kashanu.ac.ir