Experimental analysis of damage creation and permanent indentation on highly oriented plates

Abdallah, Elias Abi; Bouvet, Christophe; Rivallant, Samuel; Broll, Bernhard; Barrau, Jean-Jacques

doi:10.1016/j.compscitech.2009.02.029

Cited by 73 publications

(53 citation statements)

References 13 publications

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“…Other authors conclude that LVI and QSI are different for C/E [1,8,10,14,15,17]. Kwon and Sankar [14] and Highsmith [10] conclude that QSI leads to a larger damage zone compared to LVI, contradicting with Lagace [15] and the results of Kaczmarek [13].…”

Section: Introductioncontrasting

confidence: 52%

“…Kwon and Sankar [14] and Highsmith [10] conclude that QSI leads to a larger damage zone compared to LVI, contradicting with Lagace [15] and the results of Kaczmarek [13]. Nettles and Hodge [17] and Breen et al [8] show results that indicate QSI leads to a more than 10 % higher load compared to LVI, the opposite is seen by Abdallah et al [1] who observe a 15 % reduction in load.…”

Section: Introductionmentioning

confidence: 40%

“…[1]. For each scenario in table 2, a representative maximum displacement is obtained which is used for QSI.…”

Section: Quasi-static Indentationmentioning

confidence: 99%

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Comparing damage from low-velocity impact and quasi-static indentation in automotive carbon/epoxy and glass/polyamide-6 laminates

et al. 2018

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The results of a low-velocity impact programme on both carbon/epoxy and glass/polyamide-6 composite laminates are compared to the results of quasi-static indentation. Cross-ply and quasiisotropic stacking sequences are impacted and quasi-static indentation tests are performed up to the same maximum displacement. The response of the laminates to both test methods is compared in terms of force-displacement behaviour, dissipated energy and resulting damage. Significant differences between low-velocity impact and quasi-static indentation are found for both material systems. It is therefore concluded that the test methods cannot be interchanged for material characterisation.

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Section: Introductioncontrasting

confidence: 52%

Section: Introductionmentioning

confidence: 40%

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Comparing damage from low-velocity impact and quasi-static indentation in automotive carbon/epoxy and glass/polyamide-6 laminates

et al. 2018

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“…The maximum force attained during the impact tests is greater than the one during the quasi-static tests. The absorbed energy and damage morphology are equivalent for both tests [3].Failure at the interface is modeled by degrading stresses using two interface damage parameters corresponding to interfacial tension and shear failure, while fracture mechanics concepts are introduced by relating the total energy absorbed in the damaging process to the interfacial fracture energy [4].These authors are studying the behavior of composite structures at low-velocity impact. They are trying to give explanation and to simulate the different damage phenomena observed during the experimentation more studies are still required to have better understanding of the damage phenomena developed in these structures during the impact [5][6][7].…”

Section: Introductionmentioning

confidence: 99%

Characterization of Composite Laminates Subjected to Repeated Indentation

Kumar¹,

Prasad

Ravishankar³

et al. 2014

Advances in Materials Science

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The effect of the fiber orientation in a laminate is investigated experimentally when subjected repeated quasistatic indentation. All the laminates with different fiber orientation are subjected to indentation with a stainless steel spherical indenter of diameter 8.0mm on a universal testing machine for a maximum indenter displacement of 4mm. The rate of indenter displacement was 0.5mm/minute. Different parameters like load bearing capacity, indentation diameter, area of surface damage, etc., were recorded after 4mm of indenter displacement. All the parameters were studied and compared to evaluate the laminate with high strength.

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“…Consequently, damage tolerance in composites has been a subject of investigation for many years. Several authors, [5][6][7][8][9][10] have studied the resistance of composite structures against low velocity impacts.The use of mechanical protection against impact is one other way of solving the problem of impact on composites. Although introduction of a mechanical protection against impact induces a non-negligible increase in weight of the structure, it nonetheless avoids or considerably reduces damage in the structure.…”

mentioning

confidence: 99%

Experimental investigation of impact on composite laminates with protective layers

Rahmé

Rivallant

Fascio

et al. 2012

Composites Science and Technology

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a b s t r a c tThis paper presents an experimental study of low energy impacts on composite plates covered with a protective layer. In service, composite materials are subjected to low energy impacts. Such impacts can generate damage in the material that results in significant reduction in material strength. In order to reduce the damage severity, one solution is to add a mechanical protection on composite structures. The protection layer is made up of a low density energy absorbent material (hollow spheres) of a certain thickness and a thin layer of composite laminate (Kevlar). Energy absorption ability of these protective layers can be deduced from the load/displacement impact curves. First, two configurations of protection are tested on an aluminium plate in order to identify their performance against impact, then the same are tested on composite plates. Test results from force-displacement curves and C-scan control are compared and discussed and finally a comparison of impact on composite plates with and without protection is made for different configurations. IntroductionComposite materials are widely used nowadays in aeronautics. This growing interest is due to the relatively high strength/mass ratio of these materials compared to those of metals. These materials are sometimes subjected to low energy impacts during fabrication and in service as well which can have an influence on the residual mechanical properties of the structure [1]. In the field of aeronautics, depending on the impact detectability, damage tolerance is often the key factor in structure design [2,3]. It is a known fact that damage due to impact reduces the residual compressive strength of a structure to less than 50% of the initial strength. The notion of impact detectability was introduced for aircraft certification needs. The minimum indentation damage that can be detected by visual evaluation is called ''Barely Visible Impact Damage'' (BVID) [4], and in aeronautical standards, this threshold of detectability after few days of rest and humidity ageing is 0.3 mm depth. In the case of a non-detectable damage (indentation less than BVID), the structure must sustain the ultimate load. Consequently, damage tolerance in composites has been a subject of investigation for many years. Several authors, [5][6][7][8][9][10] have studied the resistance of composite structures against low velocity impacts.The use of mechanical protection against impact is one other way of solving the problem of impact on composites. Although introduction of a mechanical protection against impact induces a non-negligible increase in weight of the structure, it nonetheless avoids or considerably reduces damage in the structure. Furthermore, use of mechanical protection improves the detectability of impact, as the protection is generally more deformable which causes a visible post-impact indentation mark.Core material covered with skin seems to be a good candidate for protective layers. Core materials (honeycomb, foam, hollow spheres ...) are of significant scientific ...

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Experimental analysis of damage creation and permanent indentation on highly oriented plates

Cited by 73 publications

References 13 publications

Comparing damage from low-velocity impact and quasi-static indentation in automotive carbon/epoxy and glass/polyamide-6 laminates

Comparing damage from low-velocity impact and quasi-static indentation in automotive carbon/epoxy and glass/polyamide-6 laminates

Characterization of Composite Laminates Subjected to Repeated Indentation

Experimental investigation of impact on composite laminates with protective layers

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