Review Article  Open Access
Linear and Nonlinear Dynamic Analyses of Sandwich Panels with Face SheettoCore Debonding
Abstract
A survey of recent developments in the dynamic analysis of sandwich panels with face sheettocore debonding is presented. The finite element method within the ABAQUS™ code is utilized. The emphasis is directed to the procedures used to elaborate linear and nonlinear models and to predict dynamic response of the sandwich panels. Recently developed models are presented, which can be applied for structural health monitoring algorithms of realscale sandwich panels. First, various popular theories of intact sandwich panels are briefly mentioned and a model is proposed to effectively analyse the modal dynamics of debonded and damaged (due to impact) sandwich panels. The influences of debonding size, form, and location and number of such damage incidents on the modal characteristics of sandwich panels are shown. For nonlinear analysis, models based on implicit and explicit time integration schemes are presented and dynamic responses gained with those models are discussed. Finally, questions related to debonding progression at the face sheetcore interface when dynamic loading continues with time are briefly highlighted.
1. Introduction
Sandwich panels have long been recognized as one of the efficient structural elements. Due to their intrinsic properties like a high bending stiffness at minimum mass, the capability to be tailored for specific uses, high damping properties, and a great potential for energy absorption, they have found applications in diverse kinds of modern industries and structures. Along with advantages that suggest the sandwich concept, the sandwich panels suffer the consequences of their constructive features. The large differences between thicknesses and elastic moduli of the constitutive layers make the sandwich panels susceptible to debonding of the face sheet from the core at their interface. The sources of debonding usually are a result of imperfections in the manufacturing process, the degassing of the foam core under direct sunlight, the ability for water absorption of cellular types of the core followed by repeated cycles of freezing and thawing at the face sheettocore interface, lowvelocity impacts, stress concentrations due to localized loading, and so forth. The presence of debonding is often invisible, but it affects the dynamics and the strength of sandwich structures as well as it may become a reason of premature failure below the level of design loads [1]. Therefore, a correct use of sandwich panels in different engineering applications requires a better knowledge of their mechanical behaviour, in particularly, their dynamic response. This knowledge can also provide a basis for nondestructive health monitoring techniques.
In modern sandwich panels, the core layer is often made of a soft and flexible material. This leads to the core compressibility and, as a result, to the change in the height of the core during deformation [2]. Thus, to provide a highfidelity analysis of sandwich panels, the nonlinear deformation patterns in the core should be accounted for in prediction models. This makes the dynamic analysis of the sandwich panels more challenging than that of the laminates. Furthermore, high physical and geometrical mismatching is also an obstacle to handle sandwich panels using the equivalent single layer (ESL) twodimensional (2D) finite element [3, 4] or dynamic stiffness element [5] models. In this regard, models adopting mixed theories or the layerwise (LW) approach are preferable for sandwich structures [6]. The latter has given rise to a variety of highorder sandwich panels theories referred to as HSAPTs [7–9], in which the highorder effects in the sandwich panel do not result from some prior assumptions for the displacement field. These theories invite any plate/shell theory formulations for the face sheets and a 3D elasticity theory or equivalent one for the core [10–12].
One of the other aspects that relates to the analysis issues of sandwich panels is a microscopically discrete structure of the core, for example, truss cores, honeycomb cores, and corrugated or folded cores of various shapes. The traditional analysis scheme of such sandwich panels is that, first, the core is simplified as an equivalent generally anisotropic homogeneous material and then modelled by using any theory and solution method. Thus, the analysis accuracy strongly depends on correct estimations of equivalent rigidities. Some examples of finite element analyses of sandwich panels with discrete cores can be found, for example, in [13–18].
Keeping in mind the challenges in modelling sandwich structures, many efforts have been made to study their vibration responses using both linear and nonlinear models. In doing so, some studies have used the assumptions on geometrical nonlinearity in the dynamics of sandwich panels, for example, [19, 20], while the other ones have examined the influence of material nonlinearity. The effect of a viscoelastic core on damped forced oscillations has been considered, for example, in [21, 22]. The problem of the interlaminar slip between constitutive layers in the nonlinear free vibration has also been discussed, for example, in [23, 24]. Apart from these nonlinear problems, the dynamics of sandwich panels with debonding are another computationally challenging task, even when small displacements and a material linearity are assumed. The difficulties are concerned with modelling physical phenomena arising from debonding. First, the detached surfaces are free of shear and normal stresses and as a result the overall stiffness of the structure is reduced. Second, during loading or oscillations these surfaces may slip longitudinally one with respect to another and/or undergo normal compressive stress if contact between them exists. Such local changes within the debonded region give rise to alterations in the global dynamics of sandwich panels and, also, the stress fields accompanying this dynamic behaviour may result in fracture in the face sheettocore interface.
To simplify the nature of the problem, the earliest solutions on free vibration were based on the split beam approach under assumptions that the decoupled layers either freely overlap each other or are constrained to move together [25–30]. Later, improved nonlinear models excluding penetration between the layers coming into contact were developed. In [31], to prevent overlapping, the dynamics of a delaminated beam was studied using a piecewise linear virtual spring model, whereas the kinematic contact conditions were established using the nodetonode contact model in [32]. To date, a large volume of the literature on this subject is available [33]. Some recent advanced studies point at the need to use models accounting for coupling between normal and flexural actions in vibrations [34]. As found, it is a reason of parametrically induced vibration of delaminated beams and plates [35–37]. Other studies confirmed the efficiency of the LWbased finite element models compared to those using the ESL approach [38, 39] and showed that such models provide a stress recovery for localized effects [40].
Yet, the dynamic finite element analysis (FEA) contributes to developments of vibration control methods of sandwich structures [41, 42]. Alternatively, the results of the dynamic FEA of sandwich panels can be used for increasing the efficiency of the structural health monitoring (SHM). In the latter, natural frequencies, mode shapes, frequency response functions, and time or frequency domain data can be extracted from either linear or nonlinear dynamic FEA. For instance, in [43] natural frequencies extracted from the eigenvalue analysis have been used to detect and locate the saw cut within a composite plate, whereas mode shapes collected from a similar linear analysis have successfully been applied to the delamination location in a composite beam in [44]. Other authors have developed a strainbased damage index based on a linear model for the prediction of the delamination location in composite plates [45]. The curvatures of mode shapes have been utilized for quantifying the damage magnitude in a honeycomb beam in [46]. Also, a linear dynamic analysis is used in FRFbased damage detection techniques [47]. In [48] such approach has successfully been implemented for detecting debonding in a honeycomb beam. For the sake of debonding detection, the linear dynamic FEA has been carried out in [49] to highlight the relative changes of dynamic response between a healthy sandwich plate and a debonded one. More advanced techniques using modal dataset to detect debonding in sandwich structures can be found in some recent works, for example, [50–52].
Motivated by the idea to examine the influence of debonding on the modal dynamics of sandwich panels in detail, a number of numerical and experimental studies have been performed during the last two decades. For instance, in [53–55] natural frequencies and corresponding vibration modes have been calculated for flexible debonded sandwich beams. The changes of the modal characteristics in sandwich plates caused by debonding depending on the debonding size and form and of boundary conditions and sandwich core properties have been presented in [56]. Similar researches using linear models to study the dynamic behaviour of sandwich plates that have undergone a postimpact damage or containing a multidebonding have been carried out in [57–59] and [60–62], respectively. A linear model has been also adopted to examine a dynamic stability of a delaminated beam under harmonic longitudinal loading in [63]. An experimental study on the modal dynamics of a delaminated plate has been done in [64]. Changes in the peaks and valleys of the FRFs due to delamination in a honeycomb sandwich beam have been proven by experimental tests in [65]. Effects of the debonding length on fatigue and vibration of sandwich composites have been tested in [66].
Because, in general, the dynamics of composite structures are rather nonlinear, the numerical simulations could throw light on the nature of various nonlinear mechanisms, in particular, due to debonding and in turn this knowledge can make the SHM methodologies more reliable [67, 68]. Insight into the reallife dynamics of debonded sandwich panels can be gained by accounting for the “real contact” conditions between the debonded parts. Hence, nonlinear models have been developed to handle the nonlinearities caused by either of or both of the factors, namely, opening and closing of the debonding (breathing) and contact/impact between the debonded layers during vibration. In [69] the contact problem in delaminated surfaces has been modelled in terms of fictitious linear springs to study the dynamic transient behaviour of a delaminated plate. An analytical model of a 1D sandwich beam accounting for the real contact has been created in [70] to examine the influence of the contact phenomenon on the transient behaviour of the beam. In [71–73] an explicit 3D finite element contact model has been developed with ABAQUS for analysing the transient dynamics of an impacted sandwich panel. This model has also been used in [74, 75] to study the effect of the debonding size on the transient dynamic response and the stress state in sandwich plates. Other contact models addressed to discovering the role of interlaminar contact on the nonlinear dynamics of sandwich and laminated panels accounting for geometrical nonlinearity have been proposed in [76–78]. A nonlinear contact model within an implicit approach has been elaborated in [79, 80] to explore the dynamics of sandwich panels with debonding, which are subjected to harmonic forces. The research reported a complex dynamic behaviour of such panels highly dependent on the driving frequency that is inherent in structures with conditions of friction and contact [81]. A potential of such nonlinear models to identify damages in composite structures has been demonstrated in [82].
The discussion above clearly demonstrates that highfidelity dynamic finite element analysis methods of sandwich panels based on linear and nonlinear models are still needed for many engineering problems. It seems that research on the modelling aspects of the dynamics of sandwich panels with debonding is scattered across different models and diverse research areas. Often such studies exploit only one either linear or nonlinear model, and then it is not so easy to juxtapose them within the same problem being considered. Besides, many of the studies are focused on sandwich beams or unidirectional panels. This spatial reduction simplifies the nature of the physical phenomena, because it dictates a specific structural behaviour. To the best of our knowledge, there is a deficiency of 3D models for studying the dynamic behaviour of debonded sandwich plates. Some of them have been developed in our previous papers. The present work can be viewed as a comprehensive survey summarizing the recent developments in 3D finite element modelling of the dynamics of sandwich plates with debonding. Our previous findings in this research area are considered and reexamined under the light of our goal to characterize the dynamic behaviour of sandwich panels with debonding ranging from free vibration to nonlinear oscillations by both linear and nonlinear 3D finite element models. So, the present work takes a step towards the classification of computational models for quantitatively estimating the dynamics of sandwich panels with debonding and understanding the responses of such structures based on the numerical examples.
2. Outlines of Dynamic FEAs
In this section, basic aspects of the finite element procedures used in the current work to perform dynamic finite element analyses (FEAs) are briefly presented.
2.1. Equations of Motion
The finite element analysis of the system of elements provides the solution of the equations of motion corresponding to the nodal degrees of freedom, which, in general, can be written as follows [83]:where is a certain moment of time and , , , and stand for inertia, damping, and internally and externally applied forces, respectively. In the case of a linear problem, (1) reads aswhere , , and are, respectively, mass, damping, and stiffness matrices of the element assemblage and are nodal points displacements, and and are their time derivatives referring to nodal velocities and acceleration, respectively. The matrices of the physical properties of the finite elements are related to the force vectors as , , and . Under assumptions that initial conditions and boundary conditions applied to the system remain unchanged during loading, the solution of (2) completely describes a linear response of the system.
In presence of contact between elements of the system, the system response is linear, if other nonlinearities except contact do not exist, only prior to the contact conditions met. Otherwise changes in boundary conditions at a certain load level occur. Then, (2) is to be supplemented by contact constraints imposed at a set of all prospective contact pairs over the loading time as follows:and the constraints appropriate for the prescription of a Coulomb friction law, for example, as [84]In (3) and (4), and stand for normal and tangential “gap” functions defined for all active contact pairs, and are normal and tangential contact traction acting at those pairs, is a Lie derivative (a convective derivative that defines a frame invariant measure of rate of in the case of slipping), is the coefficient of friction, and is a nonnegative scalar. For conciseness, we skip details and refer to works in this area, for example, [84]. The contact traction contributes to equilibrium of the system as contact force vector acting on some nodal points at a certain moment of time t; that is, (2) takes the form
2.2. Eigenvalue Problem
Dynamic characteristics of a linear structural system (2) are governed by the natural frequencies and the corresponding mode shapes. The determination of them requires the solution of an eigenvalue problem:Hereinω is an undamped circular frequency and is the corresponding vibration mode. Then, n uncoupled solutions of (6) can be composed in the form convenient for frequency extraction:where in the matrix the columns are orthogonalized massnormalized eigenvectors and is a diagonal matrix containing squared eigenfrequencies.
2.3. ModeBased Dynamic Analysis
To provide predictions of the steadystate dynamic response of a linear system (2) due to harmonic excitation at a given driving frequency , a modal superposition method can be used. Then, in the modal subspace (2) takes the formHere the nodal displacements are expressed in terms of the vector of generalized displacements and the normal modes being found from the eigenvalue analysis; the matrices , , and are the projections of , , and onto the modal subspace; that is, and and and . In the case of linear analysis is the identity matrix, and in case of no damping coupling , where are modal damping rations. Hence, the equations in system (8) with respect to the generalized displacements are decoupled and for the rth mode have the formOnce all are evaluated, the physical response of the original system in terms of nodal displacements, velocities, acceleration, and stresses can be recovered. The analysis is done as a frequency sweep by applying the loading at a series of different frequencies and recording the system response [85].
2.4. Direct Integration Analyses
The equations in system (5) cannot be solved independently; a direct integration over time is required. One would normally resort to numerical approximation procedures to do it. The explicit central difference time integrator used in ABAQUS/Explicit [85] presents (5) at a typical time increment Δt in the formwhere is a lumped mass matrix obtained by transform of the consistent mass matrix and the velocities and the displacements are calculated at each time increment according to the expressionsThis explicit time integration scheme is conditionally stable only. An approximation to its stability limit can be achieved by evaluating the highest modal natural frequency in the FE mesh as [83].
The implicit HilberHughesTaylor (HHT) temporal integrator is used by ABAQUS/Standard [85]. This integration scheme applied to (5) yieldswhereThe unconditional stability occurs for , , and [83]. The linearized problem in (12) within the jth NewtonRaphson iteration has the formwith updating unknowns as .
2.5. Modelling Workflow
In Figure 1 the modelling workflow followed in this work is summarized. The finite element analyses carried out with ABAQUS are presented in the order of their computational cost and modelling complexity, that is, the computational procedures mentioned above and used in those analyses and some approaches and features applied to the development of linear and nonlinear models. Thereby, for sandwich panels, first, the frequency eigenvalue analysis (6) and the modalbased harmonic analysis (8) are performed using linear models and, then, the general nonlinear dynamics under an impulse load and harmonic loading are worked out using explicit (9) and implicit (12) time integration schemes. Both a debonded sandwich panel and the same healthy one are simulated in the calculations. By tracking the differences between their dynamic responses, the effects of debonding on the linear and nonlinear dynamic behaviour of the sandwich panel are evaluated. Moreover, using both linear and nonlinear models for the same sandwich panel, the impact for each of them for highlighting dynamic effects can be clearly seen.
3. Aspects of Model Discretization
The first step in a finite element analysis is the discretization process, in which the actual continuous structure is idealized as an assemblage of discrete finite elements interconnected at node. The number and type of finite elements selected for this, in essence, depend on the physical complexity of the structure and the required accuracy in the displacements and stresses [83]. In accordance with the discussion above, various theories and, as a result, modelling techniques for the FEA of sandwich panels are possible. A summary of sandwich finite element models that are available for modelling, in particular with the ABAQUS code, is collected in Table 1.
 
^{1}Classical plate theory. ^{2}Firstorder shear deformation theory. 
3.1. LayerWise Based Model
To tackle the problem at hand, the model handling the core flexibility and the transverse shear variation and the geometry and location of an embedded debonded zone has been tailored in ABAQUS using the layerwise shellsolid approach (number 5 in Table 1). This modelling strategy has been used and tested for modelling various static and dynamic problems related to sandwich panels in our previous works, for example, [10, 11, 13, 56]. In the present paper this model is revised and unified for running both linear and nonlinear analyses by switching appropriate options and/or assigning new features and properties available in the preprocessing stage and solvers of ABAQUS [85]. The main emphasis of this finite element model is that it realizes the layerwise HSAPTlike approach for the sandwich structure establishing no restrictions on the core kinematics and allowing independent moving of top and bottom skins with respect to each other. In this regard, the upper and lower skins are discretized with the eightnode 24DOF quadrilateral continuum shell elements obeying the assumptions of the FSDT theory within the ESL approach, while the core is discretized with the eightnode 20DOF hexahedral (brick) elements [85] as shown in Figure 2. The degrees of freedom (DOFs) of the brick and continuum shell elements are conveniently coupled with each other, so no additional compatibility conditions at the interface between skins and core is needed. Hence, the final governing equations of the sandwich structure assemble the displacements variables of the upper and lower skins, and the core automatically ensures the continuity of displacements at the interfaces between them. In the case of a heterogeneous core material (honeycomb), the core was replaced by an equivalent model of anisotropic material.
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A sandwich panel that has one or more arbitrary debonded regions at one or two of its skintocore interfaces is geometrically idealized using the multipartition discretization. The 3D mesh of the debonded sandwich plate consists of four different parts connected with each other through the shared nodes. These parts are discretized by applying different mesh methods and mesh densities, Figure 3. That is, a fine mesh is used for the debonded zone, the next zone surrounding the debonded one has a gradually decreasing mesh density, and a coarse mesh is introduced for the core to minimize a CPU time in calculations. In the model, the mesh size is suitable to be refined to get a required convergence. Debonding is modelled by creating a small gap (about 1% of the face sheet thickness) between the face sheet and the core. No artificial adjustment of either material properties or geometrical entities is made within the debonded region to ensure a physically real case as close as possible.
As seen in Figure 3, the finite element mode consists of two types of interfacial regions, namely, a “fully bonded zone” and a “debonded zone.” In general, the detached surfaces within the debonded region may contact each other; that is, they can slip one with respect to the other in any longitudinal direction or can come into contact/impact vertically either entirely or partially involving only some of their zones. Contact models developed using the ABAQUS code to handle the behaviour between the detached skin and core in linear and nonlinear dynamic FEAs are discussed below.
3.2. Models with Spring Element
In the modal dynamics of debonded sandwich panels, a spring element “SPRING2” is introduced between the double nodes within the debonded area (Figure 4(a)). The stiffness of the spring element is assumed to be zero in the case of tension and to be a large value in compression, that is, when the relative transverse displacement between the face sheet and the core Δu goes to zero. Since any inelastic effects are deactivated for modal analyses [85], we approximate the behaviour of the spring element by its two discrete states as shown in Figure 4(b). In such way we are able easily to activate one of the two “contact” options in the modal dynamics. That is, setting a zero stiffness to the spring elements, the contact behaviour of the detached parts is described by the free delamination model; that is, the interfaces move freely, while a nonzero stiffness value of those elements realizes the constrained delamination model between them that restrains the face sheet and the core to move together. So, a contact problem between the face sheet and core in linear dynamic FEAs is reduced to using either “mode constrained” or “modefree” delamination model [26–29]. It should be noticed that although the spring elements with given nonlinear constitutive laws enable modelling contact in a general dynamic analysis, they are less convenient for handling the debonding problem than the surface contact definition used in this work and considered below.
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3.3. Models with “Real Contact”
A general dynamic analysis enables representing “real contact” and as a result a nonlinear finite element model is addressed to considerations. In this case, between the surfaces of parts (I) and (II) within the debonded zone (Figure 3) contact definitions are imposed. The surfacetosurface contact formulation in terms of slave and master surfaces is used. The relative motion of the contacting surfaces in the contact simulation is described with small sliding kinematics that allow their separation and sliding, as shown in Figure 5. This is a reasonable assumption because of small oscillations in the debonded zone, but it is more computationally effective than a finite formulation that is especially important in the case of 3D simulations.
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The constitutive behaviour of the surfaces coming into contact in the normal direction is assumed to be governed by the “hard contact” model. The model implies that the interacting surfaces transmit no contact pressure unless the nodes of the slave surface contact the master surface and no penetration is allowed at each constraint location. In the case of friction, an isotropic Coulomb friction model is adopted to model frictional stick and slip phenomena. To resolve the contact constraints imposed on the mentioned surfaces during the dynamic analysis, appropriate contact algorithms are run in calculations. The kinematic predictor/corrector algorithm is used in the explicit dynamic FEA in the case of impulse loading, while the penalty algorithm processes contact interactions for the implicit dynamic FEA when harmonic excitations are assumed to occur. The former algorithm strictly enforces contact constraints and allows explicit updating contact forces in the calculations, Figure 6(a). The latter scheme has a weaker enforcement of contact constraints, Figure 6(b), but it is less computationally expensive than other methods available in ABAQUS, for example, the method of Lagrange multipliers. A detailed description of these contact schemes can be found, for example, in [74, 75, 79, 80]. Furthermore, the finite element models accounting for “real contact” can recover stress distributions caused by both contact/impact actions and deformations. Hence, these models can provide a strength assessment of the face sheettocore interface and, in essence, are able to estimate a possibility of separation between the core and the face sheet along their interface, where a debonding failure often initiates. However, to track the debonding progression, additional modelling efforts are needed, as shown later.
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3.4. Models of Impacted Sandwich Panels
Lowvelocity impacts induce barely visible impact damage (BVID), which may be one of the reasons for debonding occurrence in sandwich panels [86]. Therefore, the modelling of the dynamics of sandwich panels with impactinduced damage directly falls into the objectives of this work. According to the experimental findings, a sandwich plate damaged by lowvelocity impact has a combination of failure modes among which damage of the face sheet, core crushing, and face sheettocore debonding are primary. Figure 7(a) shows the key geometrical parameters of the representative crosssection of the sandwich specimen assumed to be impacted by a spherical object: the peak depth of the residual face sheet indentation, , the peak depth associated with core crushing, , the cavity (debonding), , developed between the face sheet and the core as a consequence of differences in their indentation depths and the radii of the planar dimension of the impacted face sheet, , and the crushed core, [86].
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The modelling strategy of sandwich panels which had been damaged by impact is the same as described above, except the postimpact zone itself. The damage imparted into the face sheet and the core because of an impact event is simulated by reducing elastic properties of the finite elements in the damaged regions. Appropriate reduction coefficients are used for this purpose. For the crushed core, the stiffness of elements is reduced gradually around the damaged site, as shown by a colour gradient in Figure 7(b). The residual indentations of the impacted face sheet and the crushed core are modelled as curvilinear surfaces, and the cavity between them is presented as well. The spring elements and the contact models mentioned above are introduced between appropriate surfaces of the impacted zone in the case of linear and nonlinear dynamic analyses, respectively.
4. Numerical Studies
An overview of the use of the linear and nonlinear finite elements models considered above concerning the dynamics of sandwich panels is presented in this section. In this regard, some computational examples taken from our previous works are revised and the main results are briefly discussed below.
4.1. Linear Dynamic Analyses
Example 1. To make evident the effect of “soft” core on the free vibration kinematics of the sandwich panel, the free vibration analysis of a fully bonded sandwich plate is considered first. A squared simply supported plate with a side mm and the total thickness mm has been analysed. The sandwich plate layout corresponds to a fivelayer structure 0/90/core/0/90, where face sheets are made of a composite anisotropic material, while the core is isotropic. The ratio between the face sheet and core thicknesses is 10, whereas the mismatching in material properties is the order of 10^{3} as shown in Table 2.

In the finite element mesh, one continuum shell element with the twolayer crosssection scheme across the thickness of the face sheets and five solid elements across the thickness of the core are used. In plane, the plate is discretized by 50 elements along each of its edges. Apart from the bending modes, the sandwich plate with flexible core exhibits inplane and shear (twisting) and symmetric outofplane (pumping) modes, Figure 8. For the latter modes, the core is removed from the corresponding contour plots for the better presentation of this phenomenon. The pumping modes indicate that the two face sheets move vertically in the opposite direction that relates to the changes of the plate height. Therefore, the layerwise shellsolid finite element model proposed for modelling sandwich plates with a flexible core is able to capture such nonclassical effects.
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Example 2. Firstly, the linear model with spring elements has been verified by comparing the natural frequencies and corresponding mode shapes of a debonded sandwich beam with those that are known in the literature [53]. A sandwich beam cored by foam with rectangular crosssection contains a deboned zone at its middle span, Figure 9. Material properties of the beam are listed in Table 2.
A comparison of first six natural frequencies of the debonded sandwich beam is presented in Table 3. The mode shapes associated with the appropriate natural frequencies are shown in Figure 10.
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It follows from the analysis that debonding reduces the natural frequencies compared to those of the same intact beam and this reduction is different for each mode. Apart from the global modal forms, the mode shapes of the debonded beam demonstrate both local and coupled shapes of vibration as well.
Example 3. The free vibration analysis of a sandwich plate containing a pennyshaped debonded zone is further demonstrated. The plate with a 50 mm thick foam core and each of the 2.4 mm thick face sheets is simply supported. The planar dimensions of the plate are of 270 mm by 180 mm. The radius of the debonded zone, , is of 20 mm; that is, the damage parameter defined as is about 5% of the plate area, . The material properties of each plate layer are presented in Table 2.
The influence of debonding on the modal parameters of the sandwich plate reveals, first, the change of the order of frequencies and the existence of new ones in the spectrum. This happens due to local or coupled modes relating to debonding. Second, the reduction of the low natural frequencies occurs, especially, for bending modes. Herewith, the decreasing strongly depends on the mode shape. In the case of the natural frequencies associated with inplane modes, there are practically no changes, and the changes are small for shear modes. Finally, the debonding affects the high frequencies in another manner than the lower ones, but there is no defined trend as a mode number increases. In the high part of the spectrum, there exist frequencies which are even higher than those of the intact plate; that is, the thickening phenomenon occurs [64]. The shift in natural frequencies as a result of comparing the healthy plate with the debonded one is presented in Figure 11, and several local mode shapes of the debonded sandwich plate are illustrated in Figure 12.
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Example 4. In the next step, the modebase steadystate dynamic analysis of the intact and debonded sandwich plates from the previous example is carried out. A harmonic concentrated load is applied at the centre of the bottom (undamaged in the case of the debonded plate) face sheet and the driving frequency is swept within a given frequency interval from 800 Hz to 4000 Hz. This interval was chosen to encompass the biggest part of the frequency spectrum of the plates. Frequency response functions (FRFs) calculated at the central point of the top face sheet, which have been extracted from this analysis for both intact and debonded sandwich plates, are shown in Figure 13. The difference between the FRF curves of those sandwich plates is very well visible. The shift in the resonance peaks and the existence of new ones on the FRF curve of the debonded plate are clearly demonstrated. Thus, this analysis visibly illustrates the influence of the debonding on the modal dynamics of sandwich panels; that is, both the frequency shifting and the presence of new frequencies in the frequency spectrum of the debonded plate are highlighted, as found in the previous frequency analysis.
Example 5. A sandwich plate with material properties and geometry the same as in the previous example is assumed to be impacted by a hemispherical body. Thus, the sandwich plate with the impactinduced damage such that = = 30 mm as shown in Figure 7 is analysed. The influence of each key parameter of the impacted zone on the natural frequencies of the sandwich plate is examined. The calculations showed that the frequencies are practically not sensitive to the cavity depth, the face sheet indentation, and a level of the core crushing, and only the face sheet damage level causes small visible changes in the frequency spectrum, Figure 14. Herewith, the frequencies were changing in the manner mentioned above with increasing the plane size of the impacted zone, only. That is, the latter parameter is a main factor that may manifest the impact damage within a sandwich plate if the linear model is used. It should be noted that mode shapes are more sensitive to changes of the key parameters of the impacted zone, but the differences between them are hardly recognized for each varying key parameter.
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In this regard, further, the effect of the planar size of the debonded zone, its form, location within the plate area, and number of such zones (one or two) on natural frequencies and mode shapes is studied. The different boundary conditions and core properties are considered as well.
Example 6. A simply supported rectangular sandwich plate of 180 × 135 mm^{2} with a 7 mm thick honeycomb core and each 1 mm thick CFRP face sheet is considered. A pennyshaped debonded zone is located at the plate centre between the core and the top face sheet. The damage impaired by debonding is evaluated using the parameter . The material properties of the plate constituents are listed in Table 2. To study the influence of the core type, light H100 and heavy H200 PVC foams are used as a core material in calculations, Table 2. The main conclusion of those researches is that the bigger size of debonding, the larger its influence on the modal characteristics of sandwich plates regardless of the debonding form, the core type used, and the boundary conditions applied, while each of those mentioned parameters affects the modal dynamics in a different way. Moreover, the results obtained in the eigenvalue analysis illustrate the fact that with increasing the debonding size the frequency crossover and veering phenomena can be observed for certain vibrational modes, as shown in Figure 15.
Example 7. Next, numerical investigations are performed to study the effect debonding location. A simply supported rectangular sandwich plate of 270 mm length and 185 mm width with the face sheets the same as in Example 2 and the core made of H100 PVC foam is examined. The thicknesses of the face sheets and the core are 2.4 mm and 50 mm, respectively. The plate contains either single or two equally sized pennyshaped debonded zones inflicting a total damage of . Different positions of single debonding and two equally sized debondings within the plate area are considered, as shown in Figure 16.
In Figure 17(a) one can see that the first five natural frequencies of the debonded plates are shifted more from the intact one when debonding is situated near the corner and less for centrally located debonding . The locations of debonding near the edges are intermediate cases between the mentioned two positions. Although debonding at the transverse edge more affects the frequencies, the higher modes follow the similar patterns of shifting with some exceptions for the several high modes.
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The comparative results for the debonded plate with two equally sized debondings are presented in Figure 17(b). In general, the natural frequencies and their appropriate mode shapes highly depend on the location of the two debondings within the plate area. As seen from Figure 17(b) the two debondings, located along the longitudinal midline , most affect the frequencies of the plate. In the other cases of the debonding location, it influences on the frequency changes in different ways, but in a lesser extent than in . Such tendency is retained for all modes from the lower to higher ones. More findings for this research can be found in detail in [56, 60], where this problem is better emphasized and extensively discussed with a large number of examples.
4.2. Explicit Dynamic Analysis
As mentioned earlier, the linear model is not able to account for contact and friction between the detached face sheet and core in the debonded zone, whereas nonlinear models can do it. The role of the contact behaviour on the dynamics of sandwich panels with debonding is evaluated in the next sections.
Example 8. An explicit transient dynamic analysis is carried out. In this regard, the sandwich plate with the impacted region such as in Example 3 is excited with an impulse load applied to the centre of the health bottom face sheet. In the explicit analysis, the friction coefficient, , is accepted as 0.1, and the modal damping ratio is adopted as 1% of the critical value. The comparison of results obtained for the intact and the same debonded sandwich plates clearly demonstrated a high need of accounting for “real contact” modelling to properly capture the complex dynamic effects of debonded sandwich panels. The differences in transient time histories of the longitudinal strains calculated at the central point of the impacted top face sheet and the same point of the intact plate are shown in Figure 18(a). As one can see if contact is neglected, the calculations lead to sufficiently incorrect results, which mainly overestimate the amplitude of the dynamic response. Moreover, the importance of accounting for contact increases with enlarging the size of the impacted zone, as seen in Figure 18(b).
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Besides, the computations revealed that varying the other key geometric parameters of the impacted zone (Figure 7), visible changes can also be observed in the transient response of the damaged sandwich plate, Figure 19. That is, in contrast to the modal dynamics, the transient dynamic behaviour is sensitive to all the damage factors induced by impact. However, it is difficult to evaluate the severity of each parameter. In general, the time signals obtained for two different values of the parameter are not wellcomparable between themselves. However, the debonding of bigger inplane size can be easily differentiated from the transient signals for different sizes of the debonding.
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In Figure 20 one can see that the amplitude, time lag of free decay oscillations, and attenuation (viewed as trendlines of oscillations) of displacement time curves calculated at the central plate point are clearly magnified with increasing the size of the debonded zone. This is an evidence of increasing the internal damping capacity in the debonded plate due to the presence of debonding. Thereby, the debonding introduces into the oscillations additional dissipative mechanisms caused by contact/impact and friction phenomena between the detached face sheet and core.
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Also, due to those interactions between the detached surfaces the contactinduced stresses arise in the debonded zone. These stresses may play a critical role in the localized effects and, as a result, in the global response of the sandwich plate, because they are able to contribute to development of the face sheettocore fracture mechanisms. Figure 21 shows the transient time signals of the von Mises stresses calculated at the centre and the point of boundary of the debonded zone on the top face sheet. More detailed results, regarding the transient dynamic response and the dynamic stress state occurring in the debonded sandwich plate, can be found in our papers [10, 75, 79].
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4.3. Implicit Dynamic Analysis
Example 9. To gain a deeper insight into nonlinear dynamics of sandwich plates with debonding, a longterm dynamic behaviour of a simply supported sandwich plate with a central pennyshaped debonded zone is studied. The geometrical and mechanical properties of the plate are adopted as such in Example 6. The plate is subjected to harmonic loading with a driving frequency Ω at the central point of the health bottom face sheet. A wide range of the driving frequencies defined as a fraction of the fundamental frequency of the same intact sandwich plate, , is examined. One of the main trends, which could be identified from the simulations, is the fact that the dynamic response of the debonded sandwich plate is strongly frequency dependent, as shown in Figures 22–28. The time signals are presented at either the central point of the damaged top face sheet (N1), or the central points of the debonded region between the remaining plate (N2) and the detached skin (N3) or the points near boundary of the debonded region between the remaining plate (N4) and the detached skin (N5) in a time range, when the steadystate motion of the vibrating sandwich plate has been achieved.
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Figure 22 illustrates a periodic motion of the debonded sandwich plate with the frequency the same as the excitation one. This motion goes without contact between the detached face sheet and core. That is, there are no local effects in the debonded region and global oscillations of the plate occur only.
Retaining the excitation amplitude and increasing the driving frequency lead to arising the contact behaviour between the detached segments in the sandwich plate. In Figure 23 a periodic motion of the debonded sandwich plate with one contact per each excitation is demonstrated. It is clearly seen that the periodically colliding detached surfaces produce harmonics which are integer multiples of the forcing frequency.
Although one contact per each excitation cycle also occurs in the case study shown in Figure 24, the qualitative character of response of the debonded plate differs significantly from the previous case. The dynamic behaviour of the debonded plate is a periodone motion. And, in this case the oscillations of the debonded and intact plates are not coincident in the phase. This happens because impactlike contacts prevail in the interactions between the face sheet and the remaining part of the plate. Moreover, the orbit of phase trajectory of the debonded plate is remarkably deformed due to this contact.
A periodtwo motion of the debonded sandwich plate has been detected at the driving frequency , Figure 25. The plate vibrates in such way that the detached skin and the remaining part come into contact twice per cycle of excitation. Such contacts generate both harmonics and halves of the harmonics of the excitation frequency in the spectral signals of the debonded plate.
Figure 26 presents a behaviour of the debonded plate that has no contact at the centre of the debonded zone, but there exist two contacts per each cycle of excitation at the points near the debonding boundary. It is worth noticing that the existence of such behaviour as partial contact (Figure 5(a)) has been established only due to 3D modelling of the dynamics of debonded plate. Because of such type of intermittent contact, the global dynamics of the debonded sandwich plate differs from the intact one. A phase shift between the displacement time signals of both plates is clearly seen in Figure 26(d).
The general steadystate dynamic response of the debonded plate at is demonstrated in Figure 27. One can see a quasiperiodic motion of the plate at this driving frequency. The frequency spectrum along with the peaks at integer numbers of the excitation frequency and halves of the harmonics exhibits also sidebands consisting of at least two components clearly visible on the frequencyaxis. These frequencies produced by almost regular contacts within the debonded zone are incommensurate with the excitation frequency of the external load.
The harmonic excitation of the debonded sandwich plate at the driving frequency of about 7000 Hz, that is, (), is shown in Figure 28. One can see that contacts between the remaining plate part and the detached skin are not regular. The trajectory of the debonded plate in the phase plane does not repeat itself ever again for the excitation periods. Moreover, a set of points in the Poincaré section corresponds to irregular variations of the motion from one excitation cycle to another one. From the frequency spectrum graph, one can see that the spectral spikes are surrounded by a distribution of frequencies having the character of a broadband. Thereby, the oscillations of the debonded plate at the given driving frequency look like a chaotic motion.
Although we went through each case and explained each of the dependencies found, one can highlight our papers [79, 80], which can be viewed for further insights and details in this area.
5. Further Research
Although a number of studies on the dynamic behaviour of delaminated or debonded composite panels are widely reported in literature, research on the effects of delamination or debonding on strength and damage tolerance of composite panels subjected to dynamic loading is limited. The dynamic fracture analysis of debonded sandwich panels is challenging and demands expertise in damage and fracture mechanics and material science to guide this research. For better understanding and prediction of multiple failure mechanisms occurring in sandwich structures in a dynamic environment more reliable and efficient numerical methods should be devised. The most popular methods that can be potentially used and partially have been already been applied to for this purpose are briefly discussed with only few selected references below, because, as the authors may suppose, it is a matter of future more extensive research.
5.1. Virtual Crack Closure Technique (VCCT)
The delamination/debonding growth can be modelled by the VCCT. This method is based on the Griffith crack growth criterion within the framework of the linear elastic fracture mechanics (LEFM). That is, a debonding grows if the energy released at its propagation is equal to or larger than the energy required to create a new crack surface. This critical energy release rate or fracture toughness is derived from appropriate fracture tests. The current energy release is calculated under an assumption that the energy required to extend and to close the crack over a length are identical. A progressive delamination in laminated panels under static loading has been studied using the VCCT, for example, in [87–90], whereas studies on the delamination growth with VCCT under dynamic conditions can be found in few publications only, for example, in [91, 92].
5.2. Cohesive Zone Model (CZM)
A cohesive zone model allows for simulation of both the onset and growth of delamination/debonding in one approach. It uses cohesive elements placed at the interface between constitutive layers. The elements are endowed by a certain tractionseparation law that combines a stressbased analysis to predict the onset of delamination/debonding and fracture mechanics based approach to govern its growth. In contrast to the VCCT, which uses one parameter, namely, the critical energy release rate, the CZM requires two parameters to be defined: fracture toughness and interfacial strength stresses. Modelling dynamic delamination growth in laminated panels with the CZM approach can be found, for example, in [93, 94], while the dynamic progression of debonding between the face sheet and the core in sandwich plates has been simulated with CZM, for example, in [95–97].
5.3. Extended Finite Element Method (XFEM)
The conventional finite element method is a versatile and powerful tool for the analysis of structural response of composite panels. Both the VCCT and CZM approaches can be implemented into the finite element formulation. However, the FEM uses a fixed mesh, within which the crack propagation is assumed as either releasing mesh nodes or removing finite elements. The XFEM no longer requires the mesh to be linked to discontinuities and their propagation. It uses enriched finite elements based on the partition of unity to make a complete or partial intersection of the finite element by the crack and introduces level sets to model the crack surface and the crack front, while maintaining the same mesh. Jumplike discontinuous functions are added to displacement interpolation functions for the completely intersected elements, while the elements where the crack front exists are supplemented by the asymptotic displacements fields resulting from the LEFM. The use of XFEM models for simulating quasistatic and dynamic delamination growth in laminated composites has been found, for example, in recent papers [98–100].
5.4. Peridynamics
Purpose of peridynamics is to unify the mechanics of continuous and discontinuous media within a single, consistent set of equations. This is reached with using integral equations, in contrast with the classical theory of continuum mechanics based on PDEs. In numerical implementation, the peridynamic approach is reduced to meshless and Lagrangian method, where the fracture analysis is carried out within the framework of the bondbased peridynamic theory. The latter incorporates damage in the pairwise force function allowing bonds to break when their elongation exceeds some prescribed value. After a bond breaks, it no longer sustains any force, and the endpoints are effectively disconnected from each other, and the force it was carrying is redistributed to other bonds that have not yet broken. This increased load makes it more likely that these other bonds will break too. The process of bond breakage and load redistribution, leading to further breakage, simulates cracks growth in the peridynamic model. Thus, the method enables predicting complex fracture phenomena such as spontaneous crack nucleation and crack branching, curving, and arrest. The model requires prescribed bond properties such as the stiffness constant and critical stretch, which are continuous functions of bond orientation in the principal material axes. An application of the peridynamics to predict delamination initiation and growth in laminated composites has been presented, for example, in [101, 102].
5.5. Phase Field Methods
A conceptually new computational approach to model fracture relying on phase field formulations has gained interest in recent years. Fracture phase field models make the use of a continuous scalar variable—the crack field order parameter to distinguish the fully broken and intact material phases. In such way, the sharp discontinuity is approximated through a smooth transition (diffuse transition zone) between the different values of the order parameter associated with the adjoining material phases. Thus, a crack phase field is set, while the evolution of this field due to loading models the fracture process. The description of fracture follows from the solution of a coupled nonlinear system of (quasistatic or dynamic) stress equilibrium equations and a gradienttype evolution equation for the crack phase field. Furthermore, the finite element implementation is straightforward in both two and three dimensions, using the classical FEM without any modification of initial meshes or shape functions. Examples of phase field models adopted for simulating fracture and damage in composite materials can be found, for example, in [103–105].
The commercial finite element codes which may implement these techniques are ABAQUS, ANSYS, MSC Marc, MSC Nastran, and so forth. With this implementation, the performance and accuracy of those different approaches should be systematically investigated for both the numerical competence and the adequacy of the modelled behaviour to real structural response. Consequently, their application to the progressive delamination/debonding problems in practical structures is, as yet, limited and rather is a subject of future research activity.
6. Conclusions
Debonding is an inherent potential reason for the structural failure in sandwich panels possessing the adhesively bonded structure. Hence, detailed knowledge about its influence on the dynamic behaviour of the sandwich composite is highly required. In this regard, reliable numerical prediction methods are of importance. In this paper the linear and nonlinear finite element models developed by the authors to examine the dynamics of sandwich panels with preexisting debonding are comprehensively reviewed and prospects of further investigations on this topic are briefly discussed. The structural problem at hand has been numerically solved using the ABAQUS package. Numerical results ranging from linear free and forced vibration of debonded sandwich panels to their general nonlinear dynamics accounting for contact and friction are presented. A typical sandwich plate configuration has been discretized with shell and solid finite elements in accordance with the HSAPTlike assumptions. In the modal dynamic analyses a spring finite element separated the face sheet from the core in the debonded region, while contact and friction laws representing the unique sources of nonlinearity are imposed between them in the case of general dynamic analysis.
Observations from the present work suggest the following conclusions. First, one can point out that the pumping effect or symmetric vibration modes occurring in sandwich panels with soft flexible cores can be efficiently simulated using the proposed layerwise shellsolid finite element models. This result is of importance for developing 3D models that are able to accurately predict the dynamic behaviour of debonded sandwich panels. Second, the 3D finite element models created using the mentioned modelling strategy in conjunction with spring elements are relevant for solving a range of problems of the modal dynamics of sandwich panels with both an artificial flaw embedded into the face sheet/core bond and a postimpact circular damage involving indentation, face sheet/core interface degradation and defect of core. The calculated natural frequencies and associated mode shapes have been in good compliance with results obtained by some other authors using other methods. The various parametric studies carried out in terms of debonding parameters such as size, location, and number may deserve an attention for applying these results to developing appropriate structural health monitoring techniques. The major findings from the present studies are general decreasing of natural frequencies of debonded plates compared to the same intact ones, possible thickening phenomenon, changing in the order of frequencies in the spectrum and/or appearance of new frequencies there, and potential existence of the crossover phenomenon. The steadystate modebased analyses based on the same models highlighted the occurrence of new frequencies on the frequency response curve. Meanwhile, it was observed that the mode shapes may give less useful information in the sense of debonding detection since they are highly dependent on location of the debonded zone within the plate area.
In the present paper it is also noticed that although many advances have been made in simulation and analysis of the modal dynamics of sandwich panels with damaged face sheettocore interface, the general dynamic analysis of such structures remains challenging and requires expertise in physical nature of the behaviour and accurate numerical methods applied to guide further theoretical research. Local debonding may lead to significant changes in the global dynamics such that the dynamic response may become nonlinear even under initially linear conditions. This is the next conclusion that follows from this research. Nonlinearities are mainly related to intermittent contact and friction between the detached face sheet and core during global oscillations of the plate. The present numerical studies clearly showed that, under longterm harmonic loading, the changes of the driving frequency leads to significant alterations in the type of interactions between the debonded face sheet and the remaining part and as a result the dynamic response of the sandwich plate may be either periodic, or only quasiperiodic, or even chaotic. In the case of an impulse load the major finding is that transient time history responses are very sensitive to the size and severity of the debonding. Thus, the nonlinear models’ methodology presented herein can be deemed to be a promising prediction approach for discovering a variety of physical phenomena occurring in debonded sandwich panels and for examining the effect of each of them on the dynamics at the design stage. The obtained results may give a possibility of devising new structural health monitoring techniques which are more sensitive than the ones using modal dynamics to identify the delamination/debonding damage on the structural level. Besides, the present work mentions that there is a need to extend the study of debonding on strength and damage tolerance of sandwich plates subjected to dynamic loads, because the debonding onset and the debonding evolution are critical issues to ensure a structural reliability of sandwich panels.
Conflicts of Interest
The authors Vyacheslav N. Burlayenko and Tomasz Sadowski declare that there are no conflicts of interest regarding the publication of this article.
Acknowledgments
The authors would like to mention that this research has been done within the POLONEZ 2 Project, Grant Agreement no. UMO2016/21/P/ST8/00790, supported by the National Science Centre of Poland at the Lublin University of Technology within the European Union’s Horizon 2020 research and innovation programme under the Marie SkłodowskaCurie Grant Agreement no. 665778.
References
 L. Carlsson and G. Kardomateas, Structural and Failure Mechanics of Sandwich Composites, Kluwer Academic Pub, The Netherlands, 2011.
 I. M. Daniel and E. E. Gdoutos, Major Accomplishments in Composite Materials and Sandwich Structures: An Anthology of ONR Sponsored Research, Y. D. S. Rajapakse, Ed., Springer Science+Business Media B.V., The Netherlands, 2009. View at: Publisher Site
 H. Altenbach, J. Altenbach, and W. Kissing, Mechanics of Composite Structural Elements, SpringerVerlag, Heidelberg, Berlin, Germany, 2004. View at: Publisher Site
 I. Kreja, “A literature review on computational models for laminated composite and sandwich panels,” Central European Journal of Engineering, vol. 1, no. 1, pp. 59–80, 2011. View at: Publisher Site  Google Scholar
 M. Marjanović, N. Kolarević, M. NefovskaDanilović, and M. Petronijević, “Free vibration study of sandwich plates using a family of novel shear deformable dynamic stiffness elements: limitations and comparison with the finite element solutions,” ThinWalled Structures, vol. 107, pp. 678–694, 2016. View at: Publisher Site  Google Scholar
 E. Carrera and S. Brischetto, “A survey with numerical assessment of classical and refined theories for the analysis of sandwich plates,” Applied Mechanics Reviews, vol. 62, no. 1, pp. 1–17, 2009. View at: Publisher Site  Google Scholar
 Y. Frostig and O. T. Thomsen, “Highorder free vibration of sandwich panels with a flexible core,” International Journal of Solids and Structures, vol. 41, no. 56, pp. 1697–1724, 2004. View at: Publisher Site  Google Scholar
 K. Malekzadeh and A. Sayyidmousavi, “Free vibration analysis of sandwich plates with a uniformly distributed attached mass, flexible core, and different boundary conditions,” Journal of Sandwich Structures and Materials, vol. 12, no. 6, pp. 709–732, 2010. View at: Publisher Site  Google Scholar
 D. Elmalich and O. Rabinovitch, “A highorder finite element for dynamic analysis of softcore sandwich plates,” Journal of Sandwich Structures and Materials, vol. 14, no. 5, pp. 525–555, 2012. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Dynamic analysis of debonded sandwich plates with flexible core  Numerical aspects and simulation,” Advanced Structured Materials, vol. 15, pp. 415–440, 2011. View at: Publisher Site  Google Scholar
 V. N. Burlayenko, H. Altenbach, and T. Sadowski, “An evaluation of displacementbased finite element models used for free vibration analysis of homogeneous and composite plates,” Journal of Sound and Vibration, vol. 358, pp. 152–175, 2015. View at: Publisher Site  Google Scholar
 K. R. Pradeep, B. N. Rao, S. M. Srinivasan, K. Balasubramaniam, and S. Ahamed, “Influence of core compressibility, flexibility and transverse shear effects on the response of sandwich structures,” American Journal of Mechanical and Industrial Engineering, vol. 2, no. 2, pp. 81–91, 2017. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Finiteelement free vibration and buckling analyses of sandwich plates with honeycomb and foam cores,” in Proceedings of the 2nd International Conference Nonlinear Dynamics, pp. 243–249, Kharkiv, Ukraine, 2007. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Analysis of structural performance of sandwich plates with foamfilled aluminum hexagonal honeycomb core,” Computational Materials Science, vol. 45, no. 3, pp. 658–662, 2009. View at: Publisher Site  Google Scholar
 H. Wu, J. Liu, P. Zhang, M. He, and Y. Cheng, “Numerical analysis on dynamic responses of hybrid sandwich structures with Vtype corrugated cores subjected to water impact,” in Proceedings of the OCEANS 2015  MTS/IEEE, pp. 1–5, Washington, DC, USA, October 2015. View at: Publisher Site  Google Scholar
 X. Fang, J. Wen, J. Yin, and D. Yu, “Wave propagation in metamaterial lattice sandwich plates,” in in Proceedings SPIE Health Monitoring of Structural and Biological Systems, Las Vegas, Nev, USA, 2016. View at: Google Scholar
 J.S. Yang, L. Ma, R. Schmidt et al., “Hybrid lightweight composite pyramidal truss sandwich panels with high damping and stiffness efficiency,” Composite Structures, vol. 148, pp. 85–96, 2016. View at: Publisher Site  Google Scholar
 M. Tehrani, F. H. Dezfuli, M. S. Alam, and A. S. Milani, “Parametric study on mechanical responses of corrugatedcore sandwich panels for bridge decks,” Journal of Bridge Engineering, vol. 22, no. 5, Article ID 04017002, 2017. View at: Publisher Site  Google Scholar
 D. Elmalich and O. Rabinovitch, “Geometrically nonlinear behavior of sandwich plates,” AIAA Journal, vol. 51, no. 8, pp. 1993–2008, 2013. View at: Publisher Site  Google Scholar
 F. Alijani and M. Amabili, “Nonlinear vibrations of laminated and sandwich rectangular plates with free edges. Part 1: Theory and numerical simulations,” Composite Structures, vol. 105, pp. 422–436, 2013. View at: Publisher Site  Google Scholar
 E. Hamed and O. Rabinovitch, “Modeling and dynamics of sandwich beams with a viscoelastic soft core,” AIAA Journal, vol. 47, no. 9, pp. 2194–2211, 2009. View at: Publisher Site  Google Scholar
 S. Mahmoudkhani, H. Haddadpour, and H. Navazi, “Free and forced random vibration analysis of sandwich plates with thick viscoelastic cores,” Journal of Vibration and Control, vol. 19, no. 14, pp. 2223–2240, 2013. View at: Publisher Site  Google Scholar  MathSciNet
 N. Challamel, F. Bernard, and C. Casandjian, “Outofplane behaviour of partially composite or sandwich beams by exact and Finite Element Methods,” ThinWalled Structures, vol. 48, no. 8, pp. 561–580, 2010. View at: Publisher Site  Google Scholar
 S. Lenci, F. Clementi, and J. Warminski, “Nonlinear free dynamics of a twolayer composite beam with different boundary conditions,” Meccanica, vol. 50, no. 3, pp. 675–688, 2015. View at: Publisher Site  Google Scholar
 R. L. Ramkumar, S. V. Kulkarni, and R. B. Pipes, “Free vibration frequencies of a delaminated beam,” in in Proceedings of the 34th Annual Technical Conference, Reinforced Plastic/Composite Institute, The Society of the Plastics Industry, pp. 1–5, 1979. View at: Google Scholar
 J. T. S. Wang, Y. Y. Liu, and J. A. Gibby, “Vibrations of split beams,” Journal of Sound and Vibration, vol. 84, no. 4, pp. 491–502, 1982. View at: Publisher Site  Google Scholar
 P. M. Mujumdar and S. Suryanarayan, “Flexural vibrations of beams with delaminations,” Journal of Sound and Vibration, vol. 125, no. 3, pp. 441–461, 1988. View at: Publisher Site  Google Scholar
 J. J. Tracy and G. C. Pardoen, “Effect of delamination on the natural frequencies of composite laminates,” Journal of Composite Materials, vol. 23, no. 12, pp. 1200–1216, 1989. View at: Publisher Site  Google Scholar
 M.H. H. Shen and J. E. Grady, “Free vibrations of delaminated beams,” AIAA Journal, vol. 30, no. 5, pp. 1361–1370, 1992. View at: Publisher Site  Google Scholar
 S. H. Jian and C. Hwu, “Free vibration of delaminated composite sandwich beams,” AIAA Journal, vol. 33, no. 10, pp. 1911–1918, 1995. View at: Publisher Site  Google Scholar
 H. Luo and S. Hanagud, “Dynamics of delaminated beams,” International Journal of Solids and Structures, vol. 37, no. 10, pp. 1501–1519, 2000. View at: Publisher Site  Google Scholar
 F. Ju, H. P. Lee, and K. H. Lee, “Dynamic response of delaminated composite beams with intermittent contact in delaminated segments,” Composites Part B: Engineering, vol. 4, no. 12, pp. 1211–1224, 1994. View at: Publisher Site  Google Scholar
 C. N. Della and D. Shu, “Vibration of delaminated composite laminates: a review,” Applied Mechanics Reviews, vol. 60, no. 1–6, pp. 1–20, 2007. View at: Publisher Site  Google Scholar
 A. Szekrényes, “Coupled flexurallongitudinal vibration of delaminated composite beams with local stability analysis,” Journal of Sound and Vibration, vol. 333, no. 20, pp. 5141–5164, 2014. View at: Publisher Site  Google Scholar
 A. Szekrényes, “A special case of parametrically excited systems: free vibration of delaminated composite beams,” European Journal of Mechanics  A/Solids, vol. 49, pp. 82–105, 2015. View at: Publisher Site  Google Scholar  MathSciNet
 A. Szekrényes, “Natural vibrationinduced parametric excitation in delaminated Kirchhoff plates,” Journal of Composite Materials, vol. 50, no. 17, pp. 2337–2364, 2016. View at: Publisher Site  Google Scholar
 N. H. Erdelyi and S. M. Hashemi, “On the finite element free vibration analysis of delaminated layered beams: a new assembly technique,” Shock and Vibration, vol. 2016, Article ID 3707658, 2016. View at: Publisher Site  Google Scholar
 J. Lee, “Free vibration analysis of delaminated composite beams,” Computers & Structures, vol. 74, no. 2, pp. 121–129, 2000. View at: Publisher Site  Google Scholar
 H. S. Kim, A. Chattopadhyay, and A. Ghoshal, “Characterization of delamination effect on composite laminates using a new generalized layerwise approach,” Computers & Structures, vol. 81, no. 15, pp. 1555–1566, 2003. View at: Publisher Site  Google Scholar
 A. Szekrényes, “Semilayerwise analysis of laminated plates with nonsingular delaminationThe theorem of autocontinuity,” Applied Mathematical Modelling, vol. 40, no. 2, pp. 1344–1371, 2016. View at: Publisher Site  Google Scholar
 A. Zippo, G. Ferrari, M. Amabili, M. Barbieri, and F. Pellicano, “Active vibration control of a composite sandwich plate,” Composite Structures, vol. 128, pp. 100–114, 2015. View at: Publisher Site  Google Scholar
 R. S. Kumar and M. C. Ray, “Active damping of geometrically nonlinear vibrations of sandwich plates with fuzzy fiber reinforced composite facings,” International Journal of Dynamics and Control, vol. 5, no. 2, pp. 314–336, 2017. View at: Publisher Site  Google Scholar  MathSciNet
 P. Cawley and R. D. Adams, “The location of defects in structures from measurements of natural frequencies,” Journal of Strain Analysis for Engineering Design, vol. 14, no. 2, pp. 49–57, 1979. View at: Publisher Site  Google Scholar
 C. P. Ratcliffe and W. J. Bagaria, “Vibration technique for locating delamination in a composite beam,” AIAA Journal, vol. 36, no. 6, pp. 1074–1077, 1998. View at: Publisher Site  Google Scholar
 C. Swann, A. Chattopadhyay, and A. Ghoshal, “Characterization of delamination by using damage indices,” Journal of Reinforced Plastics and Composites, vol. 24, no. 7, pp. 699–711, 2005. View at: Publisher Site  Google Scholar
 W. Lestari and P. Qiao, “Damage detection of fiberreinforced polymer honeycomb sandwich beams,” Composite Structures, vol. 67, no. 3, pp. 365–373, 2005. View at: Publisher Site  Google Scholar
 N. M. M. Maia, J. M. M. Silva, E. A. M. Almas, and R. P. C. Sampaio, “Damage detection in structures: from mode shape to frequency response function methods,” Mechanical Systems and Signal Processing, vol. 17, no. 3, pp. 489–498, 2003. View at: Publisher Site  Google Scholar
 K. Zhu, M. Chen, Q. Lu, B. Wang, and D. Fang, “Debonding detection of honeycomb sandwich structures using frequency response functions,” Journal of Sound and Vibration, vol. 333, no. 21, pp. 5299–5311, 2014. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Numerical modeling of sandwich plates with partially dedonded skintocore interface for damage detection,” in in Proceedings of the 8th International Conference on Structural Dynamics EURODYN 2011, G. De Roeck, G. Degrande, G. Lombaert, and G. Muller, Eds., pp. 2242–2249, Leuven, Belgium, 2011. View at: Google Scholar
 V. Meruane, V. del Fierro, and A. OrtizBernardin, “A maximum entropy approach to assess debonding in honeycomb aluminum plates,” Entropy, vol. 16, no. 5, pp. 2869–2889, 2014. View at: Publisher Site  Google Scholar
 V. Meruane and V. Del Fierro, “An inverse parallel genetic algorithm for the identification of skin/core debonding in honeycomb aluminium panels,” Structural Control and Health Monitoring, vol. 22, no. 12, pp. 1426–1439, 2015. View at: Publisher Site  Google Scholar
 V. Meruane, P. Véliz, E. L. Droguett, and A. OrtizBernardin, “Impact location and quantification on an aluminum sandwich panel using principal component analysis and linear approximation with maximum entropy,” Entropy, vol. 19, no. 4, 17 pages, 2017. View at: Publisher Site  Google Scholar
 H. SchwartsGivli, O. Rabinovitch, and Y. Frostig, “Free vibrations of delaminated unidirectional sandwich panels with a transversely flexible corea modified Galerkin approach,” Journal of Sound and Vibration, vol. 301, no. 12, pp. 253–277, 2007. View at: Publisher Site  Google Scholar
 I. Jayatilake, W. Karunasena, and W. Lokuge, “Effect of skincore debonding on the dynamic behaviour of GFRP composite beams,” in Proceedings of the 4th International Conference on Smart Materials and Nanotechnology in Engineering, SMN 2013, Gold Coast, Australia, 2013. View at: Publisher Site  Google Scholar
 I. Jayatilake, W. Karunasena, and W. Lokuge, “Dynamic Behaviour of Debonded GFRP Composite Beams,” Journal of Multifunctional Composites, vol. 1, no. 2, pp. 113–122, 2013. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Influence of skin/core debonding on free vibration behavior of foam and honeycomb cored sandwich plates,” International Journal of NonLinear Mechanics, vol. 45, no. 10, pp. 959–968, 2010. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Numerical studies of the dynamic behaviour of sandwich plates initially weakened by the impact damage,” in in Proceedings of the 10th Conference on Dynamical Systems  Theory and Applications DSTA, pp. 693–670, Łódź, Poland, 2009. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Free vibration of sandwich plates with impactinduced damage,” PAMM, vol. 9, no. 1, pp. 179180, 2009. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Numerical modal analysis of sandwich plates partially damaged due to impacts,” in in Proceedings of the 3rd International Conference Nonlinear Dynamics NDKhPI, pp. 284–289, Kharkiv, Ukraine, 2010. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Dynamic behaviour of sandwich plates containing single/multiple debonding,” Computational Materials Science, vol. 50, no. 4, pp. 1263–1268, 2011. View at: Publisher Site  Google Scholar
 B. Saraswathy, R. Ramesh Kumar, and L. Mangal, “Dynamic Analysis of Honeycomb Sandwich Beam with Multiple Debonds,” ISRN Mechanical Engineering, vol. 2012, pp. 1–7, 2012. View at: Publisher Site  Google Scholar
 I. Jayatilake, W. Karunasena, and W. Lokuge, “Influence of single and multiple skincore debonding on free vibration characteristics of innovative GFRP sandwich panels,” vol. 9, pp. 816–820, 2015. View at: Google Scholar
 T. Pölöskei and A. Szekrényes, “Quasiperiodic excitation in a delaminated composite beam,” Composite Structures, vol. 159, pp. 677–688, 2017. View at: Publisher Site  Google Scholar
 J. P. Hou and G. Jeronimidis, “Vibration of delaminated thin composite plates,” Composites Part A: Applied Science and Manufacturing, vol. 30, no. 8, pp. 989–995, 1999. View at: Publisher Site  Google Scholar
 H.Y. Kim and W. Hwang, “Effect of debonding on natural frequencies and frequency response functions of honeycomb sandwich beams,” Composite Structures, vol. 55, no. 1, pp. 51–62, 2002. View at: Publisher Site  Google Scholar
 M. Idriss and A. El Mahi, “Effects of debonding length on the fatigue and vibration behaviour of sandwich composite,” Journal of Composite Materials, vol. 51, no. 13, pp. 1839–1847, 2017. View at: Publisher Site  Google Scholar
 V. R. Hiwarkar, V. I. Babitsky, and V. V. Silberschmidt, “Crack as modulator, detector and amplifier in structural health monitoring,” Journal of Sound and Vibration, vol. 331, no. 15, pp. 3587–3598, 2012. View at: Publisher Site  Google Scholar
 D. Broda, W. J. Staszewski, A. Martowicz, T. Uhl, and V. V. Silberschmidt, “Modelling of nonlinear crackwave interactions for damage detection based on ultrasound  A review,” Journal of Sound and Vibration, vol. 333, no. 4, pp. 1097–1118, 2014. View at: Publisher Site  Google Scholar
 A. Chattopadhyay, H. S. Kim, and A. Ghoshal, “Nonlinear vibration analysis of smart composite structures with discrete delamination using a refined layerwise theory,” Journal of Sound and Vibration, vol. 273, no. 12, pp. 387–407, 2004. View at: Publisher Site  Google Scholar
 H. SchwartsGivli, O. Rabinovitch, and Y. Frostig, “Highorder nonlinear contact effects in the dynamic behavior of delaminated sandwich panels with a flexible core,” International Journal of Solids and Structures, vol. 44, no. 1, pp. 77–99, 2007. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “FE modeling of dynamics of impactdamaged sandwich plates with intermittent contact in detached fragments , in Aspects of fracture and cutting mechanics of materials,” Józef Jonak, pp. 71–79, 2010. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Postimpact dynamic response of sandwich plates with foam and nonmetallic honeycomb cores,” in Proceedings of the 7th European Nonlinear Dynamics Conference ENOC, D. Bernardini, G. Rega and, and F. Romeo, Eds., p. 6, Rome, Italy, 2011. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “A numerical study of the dynamic response of sandwich plates initially damaged by lowvelocity impact,” Computational Materials Science, vol. 52, no. 1, pp. 212–216, 2012. View at: Publisher Site  Google Scholar
 V. N. Burlayenko, T. Sadowski, and S. A. Nazarenko, “Numerical modeling of dynamics of sandwich plates with partially damaged facesheettocore interface,” in in Contemporary problems of mathematics, mechanics and computing sciences, N. N. Kizilova and and G. N. Zholtkevych, Eds., pp. 13–25, Publishing house PPB Virovec A.P., Kharkiv, Ukraine, 2011. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Transient dynamic response of debonded sandwich plates predicted with finite element analysis,” Meccanica, vol. 49, no. 11, pp. 2617–2633, 2014. View at: Publisher Site  Google Scholar
 A. Ghoshal, H. S. Kim, A. Chattopadhyay, and W. H. Prosser, “Effect of delamination on transient history of smart composite plates,” Finite Elements in Analysis and Design, vol. 41, no. 910, pp. 850–874, 2005. View at: Publisher Site  Google Scholar  MathSciNet
 M. Marjanović, D. Vuksanović, and G. Meschke, “Geometrically nonlinear transient analysis of delaminated composite and sandwich plates using a layerwise displacement model with contact conditions,” Composite Structures, vol. 122, pp. 67–81, 2015. View at: Publisher Site  Google Scholar
 D. Elmalich and O. Rabinovitch, “On the effect of interlaminar contact on the dynamics of locally delaminated FRP strengthened walls,” International Journal of NonLinear Mechanics, vol. 77, pp. 141–157, 2015. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Finite element nonlinear dynamic analysis of sandwich plates with partially detached facesheet and core,” Finite Elements in Analysis and Design, vol. 62, pp. 49–64, 2012. View at: Publisher Site  Google Scholar  MathSciNet
 V. N. Burlayenko and T. Sadowski, “Nonlinear dynamic analysis of harmonically excited debonded sandwich plates using finite element modelling,” Composite Structures, vol. 108, no. 1, pp. 354–366, 2014. View at: Publisher Site  Google Scholar
 E. P. Petrov, “Analysis of flutterinduced limit cycle oscillations in gasturbine structures with friction, gap, and other nonlinear contact interfaces,” Journal of Turbomachinery, vol. 134, no. 6, Article ID 061018, 2012. View at: Publisher Site  Google Scholar
 A. K. Singh, B.Y. Chen, V. B. C. Tan, T.E. Tay, and H.P. Lee, “Finite element modeling of nonlinear acoustics/ultrasonics for the detection of closed delaminations in composites,” Ultrasonics, vol. 74, pp. 89–98, 2017. View at: Publisher Site  Google Scholar
 K. J. Bathe and E. L. Wilson, Numerical Methods in Finite Element Analysis, PrenticeHall, Englewood Cliffs, NJ, USA, 1977.
 P. Wriggers, Computational Contact Mechanics, Berlin, Germany, SpringerVerlag, 2nd edition, 2006.
 “ABAQUS version 6.9 User's Manual,” Tech. Rep., ABAQUS Inc., Providence, RI, USA, 2010. View at: Google Scholar
 J. Tomblin, T. Lacy, B. Smith, S. Hooper, A. Vizzini, and S. Lee, Review of Damage Tolerance for Composite Sandwich Airframe Structures, Final Contract Report DOT/FAA/AR99/49.
 V. N. Burlayenko and T. Sadowski, “FE modeling of delamination growth in interlaminar fracture specimens,” Budownictwo i Architektura, vol. 2, no. 1, pp. 95–109, 2008. View at: Google Scholar
 A. C. Orifici and R. Krueger, “Benchmark assessment of automated delamination propagation capabilities in finite element codes for static loading,” Finite Elements in Analysis and Design, vol. 54, pp. 28–36, 2012. View at: Publisher Site  Google Scholar
 S. Samborski, “Numerical analysis of the DCB test configuration applicability to mechanically coupled Fiber Reinforced Laminated Composite beams,” Composite Structures, vol. 152, pp. 477–487, 2016. View at: Publisher Site  Google Scholar
 M. Marjanović, G. Meschke, and D. Vuksanović, “A finite element model for propagating delamination in laminated composite plates based on the Virtual Crack Closure method,” Composite Structures, vol. 150, pp. 8–19, 2016. View at: Publisher Site  Google Scholar
 Q. Qian and D. Xie, “Analysis of mixedmode dynamic crack propagation by interface element based on virtual crack closure technique,” Engineering Fracture Mechanics, vol. 74, no. 5, pp. 807–814, 2007. View at: Publisher Site  Google Scholar
 F. Magi, D. Di Maio, and I. Sever, “Validation of initial crack propagation under vibration fatigue by Finite Element analysis,” International Journal of Fatigue, vol. 104, pp. 183–194, 2017. View at: Publisher Site  Google Scholar
 L. Iannucci, “Dynamic delamination modelling using interface elements,” Computers & Structures, vol. 84, no. 1516, pp. 1029–1048, 2006. View at: Publisher Site  Google Scholar
 B. Landry and G. LaPlante, “Modeling delamination growth in composites under fatigue loadings of varying amplitudes,” Composites Part B: Engineering, vol. 43, no. 2, pp. 533–541, 2012. View at: Publisher Site  Google Scholar
 V. N. Burlayenko and T. Sadowski, “Modeling of the dynamic debonding growth of sandwich plates,” in Proceedings of the 4th International Conference on Nonlinear Dynamics NDKhPI2013, Y. V. Mikhlin and N. V. Perepelkin, Eds., pp. 225–230, Tochka Publ., Sevastopol, Ukraine, 2013. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Effects of a skin/core debond on the dynamics of impacted sandwich plates,” in Proceedings of the 12th Conference on Dynamical Systems  Theory and Applications DSTA, J. Awrejcewicz, M. Kazmierczak, P. Olejnik and, and J. Mrozowski, Eds., pp. 557–568, Łódź, Poland, 2013. View at: Google Scholar
 V. N. Burlayenko and T. Sadowski, “Simulations of postimpact skin/core debond growth in sandwich plates under impulsive loading,” Journal of Computational and Nonlinear Dynamics, vol. 3, no. 4, pp. 369–379, 2014. View at: Publisher Site  Google Scholar
 D. Motamedi and S. Mohammadi, “Dynamic analysis of fixed cracks in composites by the extended finite element method,” Engineering Fracture Mechanics, vol. 77, no. 17, pp. 3373–3393, 2010. View at: Publisher Site  Google Scholar
 J. L. Curiel Sosa and N. Karapurath, “Delamination modelling of GLARE using the extended finite element method,” Composites Science and Technology, vol. 72, no. 7, pp. 788–791, 2012. View at: Publisher Site  Google Scholar
 L. Zhao, J. Zhi, J. Zhang, Z. Liu, and N. Hu, “XFEM simulation of delamination in composite laminates,” Composites Part A: Applied Science and Manufacturing, vol. 80, pp. 61–71, 2016. View at: Publisher Site  Google Scholar
 W. Hu, Y. D. Ha, and F. Bobaru, “Modeling dynamic fracture and damage in a fiberreinforced composite lamina with peridynamics,” International Journal for Multiscale Computational Engineering, vol. 9, no. 6, pp. 707–726, 2011. View at: Publisher Site  Google Scholar
 Y. L. Hu, N. V. De Carvalho, and E. Madenci, “Peridynamic modeling of delamination growth in composite laminates,” Composite Structures, vol. 132, pp. 610–620, 2015. View at: Publisher Site  Google Scholar
 J. Cho and K.S. Lee, “Finite element simulation of crack propagation based on phase field theory,” Journal of Mechanical Science and Technology, vol. 27, no. 10, pp. 3073–3085, 2013. View at: Publisher Site  Google Scholar
 S. N. Khaderi, P. Murali, and R. Ahluwalia, “Failure and toughness of bioinspired composites: Insights from phase field modelling,” Computational Materials Science, vol. 95, pp. 1–7, 2014. View at: Publisher Site  Google Scholar
 R. Alessi and F. Freddi, “Phasefield modelling of failure in hybrid laminates,” Composite Structures, vol. 181, pp. 9–25, 2017. View at: Publisher Site  Google Scholar
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Copyright © 2018 Vyacheslav N. Burlayenko and Tomasz Sadowski. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.