Damage characterization of titanium/GFRP hybrid laminates subjected to low-velocity impact

Nakatani, Hayato; Kosaka, Tatsuro; Osaka, Katsuhiko; Sawada, Yoshihiro

doi:10.1016/j.compositesa.2011.03.005

Cited by 94 publications

(56 citation statements)

References 15 publications

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“…However, debonding affects the load transfer between the metal and composite layers, as well as the interaction between different damage modes during an impact, which makes it important in the damage process [12]. Owing to this, debonding has been implemented in the recent theoretical and finite element models in order to study low-velocity impact behaviour [6,16,[18][19][20]. However, the models have been utilized to simulate the high-energy impact response of FMLs, which includes all the different damage modes.…”

mentioning

confidence: 98%

“…The cross-sectional images after impact have indicated that debond damage forms under the impact point at the interface of the back wall metal and remaining laminate [6][7][8][9][10][11]. This particular debonding damage has been shown to form during the impactor withdrawal phase of the impact event [12,13].…”

mentioning

confidence: 99%

“…The crosssectional images have also indicated that debond damage may additionally appear at the upper metal-composite interfaces. The most evident separation is typically found in the surroundings of the impact point rather than under the impact point [6,7,14]. Depending on the fibre alignments in the laminate and on the location of the debonded interface, the shapes of the debond damage are something between oval, rectangular and circular [6,9,15].…”

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The Effects of Debonding on the Low-Velocity Impact Response of Steel-CFRP Fibre Metal Laminates

et al. 2016

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The effect of metal-composite debonding on low-velocity impact response, i.e. on contact force-central deflection response, deformation profiles and strains on the free surfaces was studied. We focused on type 2/1 fibre metal laminate specimens made of stainless steel and carbon fibre epoxy layers, and tested them with drop-weight impact and quasi-static indentation loadings. Local strains were measured with strain gauges and full-field strains with a 3-D digital image correlation method. In addition, finite element simulations were performed and the effects of debonding were studied by exploiting cohesive elements. Our results showed that debonding, either the initial debonding or that formed during the loading, lowers the slope of the contact force-central deflection curve during the force increase. The debonding formation during the rebound phase was shown to amplify the rebound of the impact side, i.e. to lower the ultimate post-impact deflection. The free surface strains were studied on the laminate's lower surface at the area outside the debond damage. In terms of in-plane strains, debonding formation during impact and indentation, as well as the initial debonding, lowered the peripheral strain and resulted in a positive change in the radial strain.

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The Effects of Debonding on the Low-Velocity Impact Response of Steel-CFRP Fibre Metal Laminates

et al. 2016

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“…The FML concept was originally proposed for fatigue critical applications. While with its development, some potential advantages over the conventional metal alloys and fiber reinforced composites in structural components applications have also been recognized, which usually in terms of the high strength and excellent resistance to impact, corrosion and moisture [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Local Reinforcement in Notched Fiber Metal Laminates by Bonding Titanium Patch

et al. 2017

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Abstract. In order to reduce the stress concentration in notched fiber metal laminate (FML) and improve its damage tolerance, the local reinforcement concept was employed in present paper. Two different reinforced structures were proposed by bonding titanium patch on single side or double sides of the standard glass fiber reinforced aluminum laminate (GLARE). Tensile tests were conducted on these reinforced GLARE, and their mechanical properties were compared for evaluating the reinforced effect of titanium patch, as well as the damage behavior which dominated the mechanical response was analysed later to capture the failure mechanism of the reinforced GLARE. The reinforced effect of titanium patch on mechanical response of GLARE laminate was usually characterized by the improvements of modulus and yield strength, as well as the significant increase of ultimate strain and strength. Cohesive failure and adhesive failure were detected in the adhesive between titanium patch and GLARE laminate, where the adhesive failure corresponded to the weak reinforced case. In addition, the variation of delamination in GLARE laminate was also closely related to the reinforced effect on mechanical response. It is expected that the present investigation can provide technical support for damage tolerance design of fiber metal laminates.

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“…The prior knowledge about force -time relationship in case of impact in laminates consisting of aluminium and fibre composite [6,7,15], facilitates the assessment of new materials in this regard by means of identical methods, which constitutes the scientific problem currently being addressed intensively [16,17].…”

Section: Introductionmentioning

confidence: 99%

Evaluation of Force-Time Changes During Impact of Hybrid Laminates Made of Titanium and Fibrous Composite

Jakubczak¹,

Surowska²,

Bieniaś³

2016

Archives of Metallurgy and Materials

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Fibre metal laminates (FML) are the modern hybrid materials with potential wide range of applications in aerospace technology due to their excellent mechanical properties (particularly fatigue strength, resistance to impacts) and also excellent corrosion resistance. The study describes the resistance to low velocity impacts in Ti/CFRP laminates. Tested laminates were produced in autoclave process. The laminates were characterized in terms of their response to impacts in specified energy range (5J, 10J, 20J). The tests were performed in accordance with ASTM D7137 standard. The laminates were subjected to impacts by means of hemispherical impactor with diameter of 12,7 mm. The following values have been determined: impact force vs. time, maximum force and the force at which the material destruction process commences (Pi). It has been found that fibre titanium laminates are characterized by high resistance to impacts. This feature is associated with elasto-plastic properties of metal and high rigidity of epoxy -fibre composite. It has been observed that Ti/CFRP laminates are characterized by more instable force during impact in stage of stabilization of impactor-laminate system and stage of force growth that glass fibre laminates. It has been observed more stable force decrease in stage of stress relaxation and withdrawal of the impactor. In energy range under test, the laminates based on titanium with glass and carbon fibres reinforcement demonstrate similar and high resistance to low-velocity impact, measured by means of failure initiation force and impact maximum force.

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Damage characterization of titanium/GFRP hybrid laminates subjected to low-velocity impact

Cited by 94 publications

References 15 publications

The Effects of Debonding on the Low-Velocity Impact Response of Steel-CFRP Fibre Metal Laminates

The Effects of Debonding on the Low-Velocity Impact Response of Steel-CFRP Fibre Metal Laminates

Local Reinforcement in Notched Fiber Metal Laminates by Bonding Titanium Patch

Evaluation of Force-Time Changes During Impact of Hybrid Laminates Made of Titanium and Fibrous Composite

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