Investigations on sandwich core properties through an experimental–numerical approach

Giglio, Marco; Manes, Andrea; Gilioli, Andrea

doi:10.1016/j.compositesb.2011.08.016

Cited by 109 publications

(49 citation statements)

References 16 publications

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“…In this region the crushing and fracture of the cores start ( Figure 5). Depending on the core densification at the end of Region 3, an increase in the compressive stress is observed, as was reported in [16][17][18][19][20][21][22][23][24] .…”

Section: Modeling Of the Cell Walls Of Honeycomb Compositessupporting

confidence: 56%

“…From the axial compression collapse tests on the aluminum honeycomb sandwich panel specimen, various potential influential parameters, i.e., the core height, core-cell thickness and panel aspect ratio, it was observed that the core height would be a crucial parameter affecting the sandwich panel's ultimate compressive strength. 18 Tsang and Lagace 19 reported the different failure mechanisms in impact-damaged sandwich panels subjected to uniaxial compressive loads. They observed that the damage propagation and final failure modes were dependent on the relative extents of the core and face-sheet damage.…”

Section: Introductionmentioning

confidence: 99%

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Experimental analysis and modeling of the buckling of a loaded honeycomb sandwich composite

Bentouhami¹,

Keskes²

2015

Mater. Tehnol.

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Sandwich panels have the best stiffness-to-lightness ratio, which is what makes them very useful in industrial applications. This paper is focused on a study of the buckling capacities of the core components under uniaxial compression. The critical buckling loads for various core densities and materials of honeycomb panels were experimentally and numerically investigated. The specimens under lateral loading showed three zones: zone 1 is the initial elastic state, followed by the plateau region in zone 2, while zone 3 shows a monotonically stiffening region, associated with the densification of the material. The effect of the core density and its materials on the behavior and the damage was highlighted. From the experiment it is clear that the buckling load of the specimens increases as the core density is increasing. In terms of stiffness and load at failure, the honeycomb sandwich panel had better mechanical characteristics than its components. The study also calculated the numerical buckling loads of the panels using the ABAQUS finite-element analysis program. The achieved experimental and numerical results were compared with each other. In conclusion, a good correlation between theory and experiment was found. Keywords: honeycomb sandwich panel, buckling analysis, compression, finite-element method, collapse Sendvi~ni paneli imajo najbolj{e razmerje med togostjo in maso. To jih dela primerne za industrijsko uporabo. Ta~lanek je usmerjen v {tudij zdr`ljivosti za upogibanje klju~nih komponent pri enoosni tla~ni obremenitvi. Eksperimentalno in numeri~no so bile preiskane kriti~ne upogibne obremenitve za razli~ne klju~ne gostote in material satastih plo{~. Vzorci, stransko obremenjeni, so pokazali tri podro~ja: podro~je 1 je za~etno elasti~no stanje, ki mu sledi podro~je platoja, tj. podro~je 2. Podro~je 3 prikazuje monotono upogibanje, povezano z zgo{~evanjem materiala. Ocenjen je bil vpliv klju~ne gostote in materialov glede vedenja in po{kodb. Iz preizkusov je razvidno, da z nara{~anjem klju~ne gostote nara{~a tudi odpornost proti upogibni obremenitvi vzorcev. Glede na upogibanje in obremenitev pri poru{itvi ima satasta sendvi~na plo{~a bolj{e mehanske lastnosti v primerjavi z njenimi komponentami. V {tudiji je tudi izra~unana numeri~na upogibna obremenitev panelov z analizo kon~nih elementov s programom ABAQUS. Primerjani so dobljeni eksperimentalni in numeri~ni rezultati. Dobljena je bila dobra korelacija med teorijo in eksperimentalnimi rezultati. Klju~ne besede: satasta sendvi~na plo{~a, analiza upogibanja, tla~enje, metoda kon~nih elementov, poru{itev

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Section: Modeling Of the Cell Walls Of Honeycomb Compositessupporting

confidence: 56%

Section: Introductionmentioning

confidence: 99%

Experimental analysis and modeling of the buckling of a loaded honeycomb sandwich composite

Bentouhami¹,

Keskes²

2015

Mater. Tehnol.

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“…Virtual test predictions agreed with experimental data, quantitatively and qualitatively, especially for compression across all materials. Giglio and co-workers [101] carried out similar virtual testing analysis as Heimbs but limited only to Nomex honeycomb core with hexagonal cell shape. Flatwise compression simulations were carried out and experimental results compared closely with predictions from these simulations.…”

Section: Figure 16mentioning

confidence: 99%

Virtual testing of advanced composites, cellular materials and biomaterials: A review

Okereke

Akpoyomare

Bingley

2014

Composites Part B: Engineering

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Please cite this article as: Okereke, M.I., Akpoyomare, A.I., Bingley, M.S., Virtual testing of advanced composites, cellular materials and biomaterials: a review, Composites: Part B (2014), doi: http://dx.doi.org/10. 1016/ j.compositesb.2014.01.007 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. AbstractThis paper documents the emergence of virtual testing frameworks for prediction of the constitutive responses of engineering materials. A detailed study is presented, of the philosophy underpinning virtual testing schemes: highlighting the structure, challenges and opportunities posed by a virtual testing strategy compared with traditional laboratory experiments. The virtual testing process has been discussed from atomistic to macrostructural lengthscales of analyses. Several implementations of virtual testing frameworks for diverse categories of materials are also presented, with particular emphasis on composites, cellular materials and biomaterials (collectively described as heterogeneous systems, in this context). The robustness of virtual frameworks for prediction of the constitutive behaviour of these materials is discussed. The paper also considers the current thinking on developing virtual laboratories in relation to availability of computational resources as well as the development of multi-scale material model algorithms. In conclusion, the paper highlights the challenges facing developments of future virtual testing frameworks. This review represents a comprehensive documentation of the state of knowledge on virtual testing from microscale to macroscale length scales for heterogeneous materials across constitutive responses from elastic to damage regimes.

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“…The basic strategy to model the individual damage mechanisms was to define the damage model for different components, respectively. To simulate the low velocity impact response of composite sandwich structure, the continuum damage mechanics based damage criteria were defined for predicting the intra-laminar damage of composite face sheet with delamination using cohesive zone elements while the mechanical behaviour of honeycomb core can be modelled, referring to the experimentally measured data (Aktay et al 2008;Liu et al 2017) or damage model for Nomex (Chen et al 2017;Liu et al 2015;Giglio et al 2012) or Aluminium honeycomb (Lee et al 2010;Kay 2003).…”

Section: Honeycomb Sandwich Structurementioning

confidence: 99%

Modelling low velocity impact induced damage in composite laminates

Shi

Soutis

2017

Mech Adv Mater Mod Process

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The paper presents recent progress on modelling low velocity impact induced damage in fibre reinforced composite laminates. It is important to understand the mechanisms of barely visible impact damage (BVID) and how it affects structural performance. To reduce labour intensive testing, the development of finite element (FE) techniques for simulating impact damage becomes essential and recent effort by the composites research community is reviewed in this work. The FE predicted damage initiation and propagation can be validated by Non Destructive Techniques (NDT) that gives confidence to the developed numerical damage models. A reliable damage simulation can assist the design process to optimise laminate configurations, reduce weight and improve performance of components and structures used in aircraft construction.

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Investigations on sandwich core properties through an experimental–numerical approach

Cited by 109 publications

References 16 publications

Experimental analysis and modeling of the buckling of a loaded honeycomb sandwich composite

Experimental analysis and modeling of the buckling of a loaded honeycomb sandwich composite

Virtual testing of advanced composites, cellular materials and biomaterials: A review

Modelling low velocity impact induced damage in composite laminates

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