Investigation of two finite element modelling approaches for ballistic impact response of composite laminates

Zhang, Xiaotian; Liu, Tao; He, Ning-bo; Jia, Guozhu

doi:10.1080/13588265.2016.1270495

Cited by 7 publications

(2 citation statements)

References 44 publications

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“…The tiebreak approach is also often used to predict damage of composite laminates [ 18 , 19 ]. Zhang et al [ 20 ] developed an impact model (uniform model) for composite materials and then used the tiebreak approach to develop a layered model. They found that the uniform model can simulate the main ballistic impact behavior of composite materials, whereas the layered model can simulate more detailed features of composite damage.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Study of Low-Velocity Impact and Tensile after Impact for CFRP Laminates Single-Lap Joints Adhesively Bonded Structure

Huang

2021

Materials

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To investigate the mechanical behavior of the single-lap joints (SLJs) adhesively bonded structure of carbon fiber reinforced polymer (CFRP) laminates under the low-velocity impact (LVI) and tensile-after impact (TAI), tests and simulations were carried out. A finite element model (FEM) was established based on the cohesive zone model (CZM) and Hashin criterion to predict the damage evolution process of adhesive film, intra- and inter-laminar of the SLJs of CFRP laminates, and its effectiveness was verified by experiments. Moreover, three different overlap lengths (20 mm, 30 mm, and 40 mm) and four different impact energies (Intact joint, 10 J, 20 J, and 30 J) are considered in the present study. Finally, the effects of different impact energies and overlap lengths on the residual strength of SLJs after impact were discussed. The results divulged that numerical results of impact and TAI processes of SLJs were in good agreement with experiment results. During the impact process, the damage of the laminates was primarily fiber and matrix tensile damage, whereas the adhesive film was damaged cohesively; the areas of damage increased with the increase of impact energy, and the normal stress of the adhesive film expanded from the edge to the middle region with the increase of impact force. The influence of LVI on SLJs adhesively bonded structures was very significant, and it is not effective to obtain a higher impact resistance by increasing the overlap length. For the tensile process, the failure mode of TAI of the SLJs was interface failure, the surplus strength of the SLJs gradually decreased with the increase of the impact energy because of the smaller overlap length, the overlap length more than 30 mm, and the low energy impact has almost no effect on the residual strength of the SLJs.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Study of Low-Velocity Impact and Tensile after Impact for CFRP Laminates Single-Lap Joints Adhesively Bonded Structure

Huang

2021

Materials

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“…These papers are all taking into consideration the complete mechanics of composite panels under impact loading [15]. In terms of numerical simulation, several researches have also been conducted [16][17]. Furthermore, the intense interest manifested by various industries -aerospace being the pioneer -in the composite materials generally and methods of testing such composite panels specifically have led to the standardization of the named methods [18][19][20].…”

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confidence: 99%

Impact Testing on Composite Panels of Fiberglass, Carbon and Kevlar-Carbon A comparison and validation study

Croitoru¹,

Oancea²,

Constantin³

2017

Mat.Plast.

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A validation study between finite element analysis and experimental testing considering an impact loading of Fiberglass, Carbon and Kevlar-Carbon composite panels of 150 x 100 mm2 was conducted by the authors. Using the design of experiments method and the Design Expert software tool, the data obtained in FEA environment is validated, through means of statistical distributions, by the experimental tests results.

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Damage modelling strategies for unidirectional laminates subjected to impact using CZM and orthotropic plasticity law

Goldoni

Mantovani

2021

Composite Structures

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Investigation of two finite element modelling approaches for ballistic impact response of composite laminates

Cited by 7 publications

References 44 publications

Experimental and Numerical Study of Low-Velocity Impact and Tensile after Impact for CFRP Laminates Single-Lap Joints Adhesively Bonded Structure

Experimental and Numerical Study of Low-Velocity Impact and Tensile after Impact for CFRP Laminates Single-Lap Joints Adhesively Bonded Structure

Impact Testing on Composite Panels of Fiberglass, Carbon and Kevlar-Carbon A comparison and validation study

Damage modelling strategies for unidirectional laminates subjected to impact using CZM and orthotropic plasticity law

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