# Adhesive joint computations using cohesive zones

- Nunziante Valoroso
^{1}Email author and - Silvio de Barros
^{2}

**1**:8

**DOI: **10.1186/2196-4351-1-8

© Valoroso and de Barros; licensee Springer. 2013

**Received: **4 October 2013

**Accepted: **3 December 2013

**Published: **30 December 2013

## Abstract

### Background

The cohesive zone approach has gained increasing success in recent years for simulating debonding and fracture via finite element methods and is ideally suited for simulating adhesive joints, the potential crack paths being generally known in advance in most cases. In the paper the determination of the size of the so-called cohesive process zone is discussed, i.e. the region wherein the stress and damage state have to be correctly resolved in order to properly quantify the dissipated energy and the load bearing capacity of the structure. An a priori estimate for the size of the active process zone is provided based on the beam on elastic foundation model in which the material parameters of the cohesive law are incorporated.

### Methods

The formulation of the cohesive model in a damage mechanics format is first provided. The beam on elastic foundation model is then recalled and an approximate solution for the cohesive zone length is found that depends on a material length and a geometric parameter as well.

### Results and discussion

Numerical results are presented for a Double Cantilever Beam (DCB) geometry with varying thickness for which bilinear and exponential cohesive laws are considered. The influence of the geometry and of the shape of the cohesive law are put forward in terms of global response and evolution of the cohesive process zone.

### Conclusions

The size of the process zone is found to be quite sensitive to the specimen characteristic size, whose influence is well captured even using a simplified modeling wherein the original cohesive law is changed into an ideal perfectly brittle one. This leads to fairly good estimates of the size of the cohesive zone compared to finite element results.

### Keywords

Adhesive joints Cohesive zone Interface elements## Background

Recent advances in adhesive bonding technologies have led to a rapid growth in the use of structural adhesives and in many cases their use is by far more convenient than traditional joining methods [1, 2]. Namely, a major advantage of structural adhesive joints is that they provide more uniform stress transfer compared to other types of fastening systems; however, most adhesive bonds contain defects such as voids, regions with no or poor bonding and micro cracks, and such defects might grow under loading and give rise to local decohesion and formation of macro fractures.

To a great extent, at the onset of decohesion in a bonded joint the surface tractions between the joined adherends do not suddenly drop to zero owing to the presence of low-range interactions that precede the formation of traction-free surfaces. Such interactions can be effectively described by allowing jumps in the displacement field along an interface where crack propagation is known or is expected to occur. At each point of the interface such displacement discontinuities have then to be related to surface tractions components via a decohesion model, i.e. a relationship able of representing the different phases of the potential debonding process from the initial undamaged condition to progressive damage and up to fracture propagation. The driving idea for such a class of models is the cohesive-zone concept initially introduced by Barenblatt [3] and Dugdale [4]. This approach has gained major popularity in recent years for simulating delamination, debonding, fracture and fragmentation via finite element methods and is ideally suited for simulating adhesive joints, the potential crack paths being generally known in advance in most cases, see e.g. [5, 6] and references therein for recent survey accounts.

Adhesive joints may be loaded to failure in the design configurations or in the form of test specimens and it is important to fully understand the response obtained by such testing especially for the apparently simple configurations used in international standards since fracture behavior is in general governed by material properties, loading conditions and geometrical parameters as well. Moreover, apart from being employed for studying sensitivity and data reduction [7, 8], simple joint configurations can be interpreted on a theoretical basis to define requirements for elements and for the mesh that guarantee meaningful answers from numerics. This is indeed a crucial point since it has a direct impact on the results of computations.

In this paper one of such critical aspects of finite element analysis of adhesive joints is discussed, i.e. the estimation of the size of the cohesive process zone. This is the region wherein the stress and damage state must be correctly resolved to properly quantify the dissipated energy and the load bearing capacity of the structure.

It is well known that a cohesive model brings a length scale into the problem in the form of a characteristic length parameter; this expresses the length over which the cohesive constitutive relation plays a role. A recent survey about length scales in the simulation of delamination and fracture can be found in [9]; worth mentioning is also Reference [10], where is provided a table comparing the different expressions proposed in the literature to estimate the cohesive zone extension.

Based on a simplified modeling, in the present work an a priori estimate for the size of the active process zone under mode-I conditions, and for the size of the nearby region subject to compressive stresses as well, is provided. To this end use is made of a beam on elastic foundation model in which the material parameters of the cohesive law are incorporated. The expressions obtained that quantify the extension of the cohesive zone are fairly accurate and very easy to implement. This is demonstrated through numerical experiments in which we consider two different shapes of the traction-separation law and simulate two symmetric double cantilever beam (DCB) fracture specimens with different characteristic geometric size.

## Methods

### Cohesive model

**t**and the displacement jumps [[u]] = u

^{+}- u

^{-}, and on a damage criterion for the cohesive process zone growth and the crack advancement. In particular, in the following we refer to the model originally presented in [11] and consider the only one-dimensional (mode I) case, that is governed by the following equations:

In the above relationships *t* and *Y* respectively denote the interface traction and the damage-driving force, *D* ∈ [0, 1] is the scalar damage variable, [[*u*]] is the displacement jump in the direction normal to the interface, 〈·〉_{±} indicates the positive (negative) parts of the argument while *k* and *k*^{-} are the undamaged interface stiffness parameters in tension and compression, respectively.

*F*, typically a power law or an exponential, whose explicit expression is constructed in a way to ensure that the energy dissipated in the formation of a new unit traction-free surface equals the adhesive fracture energy

*G*

_{ c }. In particular, the exponential traction-separation relationship given in [11] can be obtained using:

*τ*the damage variable can be obtained as:

### Beam on elastic foundation model

The idea of using the beam on elastic foundation model to analyze adhesively bonded specimens is not new. In earlier applications it has been employed in the form of the one-parameter Winkler model to compute corrections factors for the DCB specimen for data reduction based on beam theories [12], see also [13].

*x*> 0 can be expressed as:

*λ*is the reciprocal of the model wavelength given as:

*h*being the thickness of the DCB arm and

*E*the elastic modulus of the bulk material. Obviously, the free arm of the beam -

*a*<

*x*< 0 has a cubic solution since there is no distributed load. The parameter (6) has the dimensions of a length that results from the product of a material length and a geometric dimension. Actually, the interface elastic stiffness ratio

*E*/

*k*is proportional to the characteristic length parameter of the cohesive law provided in [15] as:

*A*and

*B*in Equation (5) are computed from boundary conditions. Their simplest expression is obtained using the boundary conditions on the shear force and the bending moment at

*x*=0 to get:

*u*(

*x*) = 0 that, on account of (9), can be expressed as:

*n*≥ 0. Relationship (10) applies provided that the constitution of the interface is linear. An approximate solution for a nonlinear interface model can however be obtained by changing the shape of the cohesive relationship into a virtually perfectly brittle law that preserves either the interface stiffness

*k*or the peak stress

*t*

_{ max }of the nonlinear law. In the first case the beam length parameter has the expression (6) and the maximum stress of a brittle law with the same fracture energy increases to the value

In closing this section we remind that, apart from the factor (2/3)^{1/4}≃0.9, the expression (12) is usually taken to represent the length of the cohesive damage zone in slender composite laminates [16].

## Results and discussion

The cohesive model summarized in the previous Section has been implemented in a customized version of the finite element code FEAP [17]. For the computations described in this section use has been made of enhanced assumed strain quadrilaterals for the bulk material and 4-noded interface elements.

As a numerical example we refer to the classical DCB geometry under plane strain conditions. Loading is simulated via displacement control and either a bilinear or an exponential cohesive law are considered. For results to be comparable the same critical fracture energy *G*_{
c
} = 0.125 N/mm and peak stress *t*_{
max
} = 10 N/mm^{2} have been taken as material parameters for the interface, which are representative of a thin epoxy adhesive film (≃ 0.2 mm thick) bonded on an aluminum substrate. Elastic moduli for the bulk material (aluminum alloy) are *E* = 70 GPa and *ν* = 0.3. The specimen length is *L* = 200 mm, the initial flaw is *a* = 50 mm and the arm height is taken as *h* = 8 mm for the thin beam and *h* = 80 mm for the thick case. Unlike the thin beam, which corresponds to the geometry that has been experimentally tested in [5], the thick beam case is a pure numerical exercise aiming to reproduce a stiff structure for which the size of the cohesive zone is comparable to the dimensions of the sample, see also [18].

*l*

_{ coh }of the cohesive process zone is found to be more sensitive to the shape of the cohesive law. In both examined cases, a steady state is attained for a load level close to the peak load and using finite element analysis the size of the damage cohesive zone is found to be

*l*

_{coh,exp}= 9.28 mm for the exponential cohesive law and

*l*

_{coh,bil}= 7.23 mm for the bilinear one.

From the beam on elastic foundation model the size of the cohesive zone follows from relationship (10) for *n* = 0, i.e. as the first zero of the deflection function (5), whereby one obtains a length *x*_{0} = 11.8 mm when using the stiffness-preserving wavelength (6) and *x*_{0} = 6.31 mm when expression (12) is adopted instead. The interval defined by these values clearly delimits the length of the damage cohesive zone computed via finite elements whereas the material length parameter defined in (7) is computed as *l*_{
c
} = 87.5 mm, which is quite far from the numerical solution. As for the size of the region subject to compressive stresses ahead of the crack front, from finite element computations one obtains a length of about 30 mm while from (10) one obtains *x*_{1} - *x*_{0} = *π* / *λ* ∈[25.6, 41.3] mm, which again includes the numerically computed value.

*h*of the arms of the DCB is increased from 8 mm to 80 mm while material properties are kept the same as for the thin specimen. In this case the differences in the computed solutions obtained with the two cohesive models are more apparent for both the load-deflection curves and the extension of the cohesive zone, see Figure 4.

For the case at hand of the thick specimen, no steady state is reached in the evolution of the cohesive zone size that starts decreasing right after the peak load has been attained. The maximum length for the damage cohesive zone computed via finite element analysis is found to be *l*_{coh,exp} = 63.5 mm for the exponential cohesive law and *l*_{coh,bil} = 39.2 mm for the bilinear one whereas from the Winkler model the size of the cohesive zone is estimated either as *x*_{0} = 44.5 mm if the wavelength is computed using (6) or as *x*_{0} = 87.8 mm when referring to (12). Obviously, the length parameter (7) is the same as before since, by definition, it is independent from the specimen size. As for the size of the region subject to compressive stresses ahead of the crack front, it is numerically found to extend up to the right free end of the specimen. This is confirmed from (10) as well, whereby it is estimated as *x*_{1} - *x*_{0} = *π* / *λ* ∈[130.6, 232.2] mm, which practically exceeds the specimen length.

Based on the previous results one could conclude that the size of the cohesive process zone is captured fairly well for both the thin and thick DCB cases, which demonstrates the importance of using an estimate that includes a geometric parameter in addition to the material length scale (7). Despite the intrinsic limitations of the adopted simplified modeling, that basically relies upon linear elastic considerations, the a priori estimates for the size of both the cohesive zone and of the compressed region ahead of the crack front seem to be reliable especially for the thin DCB case. On the contrary, for the thick DCB a priori estimates do not compare well as in the previous case; this is likely to occur because for the thick DCB the cohesive zone is not completely developed since the beam cannot be considered long compared to the model wavelength.

## Conclusions

A simplified modeling for estimating the cohesive zone size in mode-I debonding problems across a range of geometrical properties has been presented. In particular, it is shown that the size of the damaged zone and that of the region subject to compressive stresses ahead of the crack front can be estimated with good approximation as functions of the cohesive parameters and of the specimen geometry via a beam on elastic foundation model. Unlike the global load-deflection response, for a given characteristic length of the traction-separation law the size of the process zone is found to be quite sensitive to the specimen characteristic size, whose influence is well captured even using a simplified modeling.

In the present paper comparisons between finite element results and the beam model have been carried out by modifying the shape of the cohesive law in a way to preserve either the initial stiffness or the peak stress. This has led to fairly good estimates of the size of the cohesive zone. In the Authors’ opinion the subject is worth investigating and alternative strategies to improve the predictive capabilities of the present approach will be examined in forthcoming papers.

## Declarations

## Authors’ Affiliations

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## Copyright

This article is published under license to BioMed Central Ltd. This is an Open Access article distributed under the terms of the Creative Commons Attribution License(http://creativecommons.org/licenses/by/2.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.