An efficient numerical approach to the prediction of laminate tolerance to Barely Visible Impact Damage

Baluch, Abrar H.; Falcó, O.; Ubago-Jiménez, José Luis; Tijs, B.H.A.H.; Lopes, C.S.

doi:10.1016/j.compstruct.2019.111017

Cited by 47 publications

(17 citation statements)

References 44 publications

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“…Salvetti et al [ 14 ] developed a model based on the dynamic method and considering stiffness degradation to predict the load–displacement curve during impact. Baluch et al [ 15 ] mapped the relevant barely visible impact damage characteristics to an efficient CAI finite‐element model based on continuous shell discretization, which improved the computational efficiency of CAI strength prediction. Ebina et al [ 16 ] proposed an algorithm including cohesive zone model (CZM), continuous damage mechanics model, and smeared crack model, which clearly presented different damage modes.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on behaviors of composite laminates with initial delamination defects under impact and compression after impact

et al. 2022

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The initial delamination defects may arise during the preparation of carbon fiber-reinforced polymer (CFRP) composite laminates, so its effects need to be considered in the evolution of mechanical properties. In this article, the behaviors of composite laminates with initial delamination defects under impact and compression after impact (CAI) are investigated by numerical method. The simulation framework composed of the micromechanics of failure (MMF) theory and the mixed mode exponential cohesive zone model (ECZM) is constructed. The numerical analysis compares the effects of the interaction between four different initial delamination defects and impact loading on impact response and CAI strength at two impact velocity levels (1.336 and 2.314 m/s). Furthermore, the failure mechanisms of laminates with initial delamination defect are disclosed under CAI loading. The findings indicate

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Section: Introductionmentioning

confidence: 99%

Numerical investigation on behaviors of composite laminates with initial delamination defects under impact and compression after impact

et al. 2022

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“…Impact events, including high-and low-velocity events, often damage equipment. In general, the damage caused by high-velocity impact events is visible impact damage, whereas low-velocity impact can cause barely visible impact damage (BVID), posing a serious threat to the operational safety of the equipment [1,2]. Events, such as the sudden fall of a component or an unexpected hit from a foreign object, can cause impact damage to the equipment.…”

Section: Introductionmentioning

confidence: 99%

Error-Index-Based Algorithm for Low-Velocity Impact Localization

Peng

Cui

Huang

et al. 2022

Shock and Vibration

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Flat plates and cylindrical shells are commonly used in large equipment. To locate the low-velocity impact points in these structures, this study proposes an error-index-based algorithm for impact localization. The time of arrival of an impact-generated A0 Lamb waves was first estimated based on the energy of the signal. Equations for calculating the error indices were proposed for flat-plate and cylindrical shell structures, and the probability distribution functions of the impact points are constructed for visual localization. The impact test results on a flat plate and cylindrical shell indicated that, compared to the Morlet wavelet method, the proposed algorithm improved the mean relative error of impact point localization on the flat plate by 0.22%, 15.64%, and 15.26% under three different noise conditions, respectively (i.e., no noise, and SNR = 5 and 0 dB). For the cylindrical shell, the mean relative error of impact localization improved by 1.8%, 3.97%, and 28.12% under the three conditions, respectively. The results indicated that the proposed localization algorithm can accurately locate the impact points on a flat plate and cylindrical shell, even under strong background noise conditions, providing a reference for future research on locating low-velocity impact points in large equipment.

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“…Carbon fiber reinforced polymer (CFRP) laminate single-lap joints (SLJs) structure has become the core part of automobile and aircraft structure because of its small number of components, lightweight design, and high connection efficiency [ 1 , 2 , 3 , 4 ]. In the process of fabrication, use, and maintenance, CFRP laminate SLJs adhesively bonded structure are inevitably subjected to low-velocity impact (LVI), resulting in various damages, including matrix damage, fiber damage, and delamination damage, known as barely visible impact damage (BVID) [ 5 , 6 , 7 ], which severely affects the integrity, residual strength, and service life of SLJs. Borba et al [ 8 ] investigated the effect of different impact energies on the residual strength of friction riveted joints based on an experimental approach.…”

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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An efficient numerical approach to the prediction of laminate tolerance to Barely Visible Impact Damage

Cited by 47 publications

References 44 publications

Numerical investigation on behaviors of composite laminates with initial delamination defects under impact and compression after impact

Numerical investigation on behaviors of composite laminates with initial delamination defects under impact and compression after impact

Error-Index-Based Algorithm for Low-Velocity Impact Localization

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

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