Dynamic behaviour of sandwich plates containing single/multiple debonding

Burlayenko, Vyacheslav N.; Sadowski, Tomasz

doi:10.1016/j.commatsci.2010.08.005

Cited by 34 publications

(21 citation statements)

References 16 publications

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“…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.…”

Section: Examplementioning

confidence: 95%

“…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][58][59] and [60][61][62], respectively. A linear model has been also adopted to examine a dynamic stability of a delaminated beam under harmonic longitudinal loading in [63].…”

Section: Introductionmentioning

confidence: 99%

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Linear and Nonlinear Dynamic Analyses of Sandwich Panels with Face Sheet‐to‐Core Debonding

Burlayenko

2018

Shock and Vibration

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A survey of recent developments in the dynamic analysis of sandwich panels with face sheet-to-core debonding is presented. The finite element method within the ABAQUS6 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 real-scale 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 sheet-core interface when dynamic loading continues with time are briefly highlighted.

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Section: Examplementioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Linear and Nonlinear Dynamic Analyses of Sandwich Panels with Face Sheet‐to‐Core Debonding

Burlayenko

2018

Shock and Vibration

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“…On the other hand, modeling vibrations in sandwich structures with debonding is generally accompanied by contact problems between the interfaces of the debonded region [52]. Burlayenko and Sadowski [7,8] modeled the debonded region by creating a small gap between the face and the core and by introducing bi-linear spring elements between the double nodes in the debonded area. The springs have a stiffness equal to zero in tension and a large value in compression, simulating a contact condition.…”

Section: Skin Honeycomb Corementioning

confidence: 99%

“…Many studies have demonstrated that vibration characteristics are sensitive to delamination even if the delamination is located in hidden or internal areas [3,4]. Nevertheless, there have only been a few studies related to the debonding of sandwich structures [5][6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

A Maximum Entropy Approach to Assess Debonding in Honeycomb aluminum Plates

Meruane

Fierro

Ortiz-Bernardin

2014

Entropy

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Honeycomb sandwich structures are used in a wide variety of applications. Nevertheless, due to manufacturing defects or impact loads, these structures can be subject to imperfect bonding or debonding between the skin and the honeycomb core. The presence of debonding reduces the bending stiffness of the composite panel, which causes detectable changes in its vibration characteristics. This article presents a new supervised learning algorithm to identify debonded regions in aluminum honeycomb panels. The algorithm uses a linear approximation method handled by a statistical inference model based on the maximum-entropy principle. The merits of this new approach are twofold: training is avoided and data is processed in a period of time that is comparable to the one of neural networks. The honeycomb panels are modeled with finite elements using a simplified three-layer shell model. The adhesive layer between the skin and core is modeled using linear springs, the rigidities of which are reduced in debonded sectors. The algorithm is validated using experimental data of an aluminum honeycomb panel under different damage scenarios.

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“…Their results showed that natural frequencies are good indicators of the presence of debonding. The finite element method was also used by Burlayenko et al [5,6] to study the influence of skin/core debonding on the vibrations of honeycomb panels, concluding that the size of the debonded zone reduces the natural frequencies and creates a discontinuity in the mode shapes. Similar conclusions have been found in the experimental and theoretical/numerical investigations of Kim and Hwang [7] and Lou et al [8], where it was concluded that natural frequencies decrease due to loss of stiffness caused by local damage and that vibration modes show local deformation in the damaged region.…”

Section: Introductionmentioning

confidence: 99%

Modal Strain Energy-Based Debonding Assessment of Sandwich Panels Using a Linear Approximation with Maximum Entropy

Meruane

Lasen

Droguett

et al. 2017

Entropy

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Sandwich structures are very attractive due to their high strength at a minimum weight, and, therefore, there has been a rapid increase in their applications. Nevertheless, these structures may present imperfect bonding or debonding between the skins and core as a result of manufacturing defects or impact loads, degrading their mechanical properties. To improve both the safety and functionality of these systems, structural damage assessment methodologies can be implemented. This article presents a damage assessment algorithm to localize and quantify debonds in sandwich panels. The proposed algorithm uses damage indices derived from the modal strain energy method and a linear approximation with a maximum entropy algorithm. Full-field vibration measurements of the panels were acquired using a high-speed 3D digital image correlation (DIC) system. Since the number of damage indices per panel is too large to be used directly in a regression algorithm, reprocessing of the data using principal component analysis (PCA) and kernel PCA has been performed. The results demonstrate that the proposed methodology accurately identifies debonding in composite panels.

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Dynamic behaviour of sandwich plates containing single/multiple debonding

Cited by 34 publications

References 16 publications

Linear and Nonlinear Dynamic Analyses of Sandwich Panels with Face Sheet‐to‐Core Debonding

Linear and Nonlinear Dynamic Analyses of Sandwich Panels with Face Sheet‐to‐Core Debonding

A Maximum Entropy Approach to Assess Debonding in Honeycomb aluminum Plates

Modal Strain Energy-Based Debonding Assessment of Sandwich Panels Using a Linear Approximation with Maximum Entropy

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