Experimental analysis and simulation of low-velocity impact damage of composite laminates

Falcó, O.; Lopes, C.S.; Sommer, Drew E.; Thomson, Daniel; Ávila, R.L.; Tijs, B.H.A.H.

doi:10.1016/j.compstruct.2022.115278

Cited by 43 publications

(18 citation statements)

References 50 publications

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“…At least three specimens were tested for each energy level according to the ASTM D7136/D7136M-20 standard. Because the repeatability of the drop-weight impact test is acceptable, only one sample for impact energy value was used [ 31 ]. Finally, the nondestructive inspection characterizations were assessed by ultrasound C-scanning systems (Olympus NDT 2.10R25).…”

Section: Materials and Experimental Setupmentioning

confidence: 99%

Research on Low-Velocity Impact Response of Novel Short-Fiber-Reinforced Composite Laminates

Huang

EShun

et al. 2023

Polymers

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Short-fiber-reinforced polymers (SFRPs) based on unidirectionally arrayed chopped strands (UACSs) have excellent formability and outstanding mechanical response. The low-velocity impact response, such as the delamination, damage tolerance and energy absorption of UACS composites, are essential to guarantee the stability and safety of composite components in service. The current study investigates the low-velocity impact response of continuous carbon-fiber-reinforced polymer (CFRP) and UACS laminates with vertical slits under drop-weight impact with various impact energies (4, 7 and 11 J). The in-plane size of the studied samples is 100 mm × 100 mm, and the stacking sequence is [0/90]4s. The time–history curves of load and energy are examined during low-velocity impact experiments, as well as the nonvisible damages are obtained by ultrasound C-scan imaging technique. A user-defined subroutine VUMAT, including the Johnson–Cook material and failure model, which is used to simulate the elastic–plastic property of the slits filled with resin, is coded in ABAQUS/Explicit. According to C-scan inspections of the impact-damaged laminates, UACS specimens show more severe delamination as impact energy increases. The damaged area of continuous CFRP laminates under impact energy of 11 J is 311 mm2, while that of UACS laminates is 1230 mm2. The slits have a negative effect on the load-bearing capacity but increase the energy absorption of UACS laminates by approximately 80% compared to the continuous CFRP laminates at 7 J. According to the variables of different damage modes in numerical simulation, cracks appear at the slits and then expand along the direction perpendicular to the slits, leading to the fracture of fiber. Nevertheless, as the damage expands to the slits, the delamination confines the damage propagation. The existence of slits could guide the path of damage propagation.

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Section: Materials and Experimental Setupmentioning

confidence: 99%

Research on Low-Velocity Impact Response of Novel Short-Fiber-Reinforced Composite Laminates

Huang

EShun

et al. 2023

Polymers

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“…Once the maximum stress criterion is exceeded, the crack initiates then the propagation is controlled by another propagation criterion which ensures that the correct amount of energy is absorbed by each element. 18 CZM technique has been commonly used in modeling interface strength like delamination, 19,20 adhesive bonding 21,22 and more specifically skin-stringer separation. 23,24 In general, failure in a composite structure is the combination of different damage mechanisms, where the crack paths are not always identifiable, hence more versatile numerical methods have been developed.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of damage evolution in carbon fiber reinforced polymer stiffened panel in post-buckling regime

Bouslama

Maslouhi

Masson

2022

Journal of Composite Materials

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Stiffened composite panels have been extensively used thanks to their ability to withstand high load and large deflection. However, their nonlinear behavior and complex damage modes during the post-buckling regime remain challenging and still require research work to improve understanding. In the current study, the buckling and post-buckling responses of a hat-stiffened panel made with carbon fiber reinforced polymer composite material are investigated experimentally and numerically with identifying the damage process and its effect on the panel stiffness. The experimental analysis is achieved by performing quasi-static multi-step compressive loading up to failure with full displacement assessment. A Structural Health Monitoring strategy is also deployed for registering and localizing the Acoustic Emission (AE) activities during each run. Matrix data extracted from the AE waveforms are processed and classified with respect to damage mechanism. Additionally, this research proposes predictive Finite Element Model based on Progressive Failure Analysis. Modified Chang-Chang failure criteria is adopted and implemented using Ansys Usermat subroutine. Numerical and experimental data have been compared and good agreement is demonstrated.

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“…The damage is difficult to detect since it often leaves no visible indication on the surface. This undetectable damage can continuously grow in the subsequent use, leading to a decline in mechanical properties and potential failure [ 7 , 8 , 9 , 10 , 11 , 12 ]. Three-dimensional woven composites can effectively overcome the delamination behavior depending on the through-thickness binder yarns in comparison with traditional laminated composites, and their impact resistance and damage tolerance are improved [ 13 , 14 , 15 , 16 , 17 , 18 , 19 , 20 ].…”

Section: Introductionmentioning

confidence: 99%

Micromechanisms and Characterization of Low-Velocity Impact Damage in 3D Woven Composites

et al. 2022

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Low-velocity impact (LVI) damage of 3D woven composites were experimentally and numerically investigated, considering different off-axis angles and impact energies. The impact responses were examined by LVI tests, and the damage morphology inside the composites was observed by X-ray micro-computed tomography (μ-CT). Yarn-level damage evolution was revealed by developing a hybrid finite element analysis model. The results show that the impact damage has significant directionality determined by the weft/warp orientation of the composites. The damage originates at the bottom of the impacted area and then expands outwards and upwards simultaneously, accompanied by in-plane and out-of-plane stress transfers. The straight-line distributed weft/warp yarns play an important role in bearing loads at the beginning of loading, while the w-shape distributed binder warp yarns gradually absorb impact deformation and toughen the whole structure as the loading proceeds. The effect of directional impact damage on post-impact performance was explored by performing compressing-after-impact (CAI) tests. It is revealed that the CAI properties along principal directions are more sensitive to the low-velocity impact, and the damage mode is significantly affected by the loading direction.

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Experimental analysis and simulation of low-velocity impact damage of composite laminates

Cited by 43 publications

References 50 publications

Research on Low-Velocity Impact Response of Novel Short-Fiber-Reinforced Composite Laminates

Research on Low-Velocity Impact Response of Novel Short-Fiber-Reinforced Composite Laminates

Experimental and numerical investigation of damage evolution in carbon fiber reinforced polymer stiffened panel in post-buckling regime

Micromechanisms and Characterization of Low-Velocity Impact Damage in 3D Woven Composites

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