Nonlinear compressive stiffness in impacted composite laminates determined by an inverse method

Sztefek, Pavel; Olsson, Robin

doi:10.1016/j.compositesa.2008.12.002

Cited by 37 publications

(18 citation statements)

References 14 publications

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“…A comparative experimental study of impact damage and corresponding artificial delaminations demonstrated significant growth of the artificial delaminations but very limited growth of the delaminations in impact damage zones (15) . These findings for impact damage zones are supported by other experimental studies (19,20) . A detailed study by X-ray tomography demonstrated increasing crack opening and limited growth of cracks within the impact damage zone, but no growth outside the initial boundaries (5) .…”

Section: Olsson Modelling Of Impact Damage Zones In Composite Laminatsupporting

confidence: 90%

“…A detailed FE analysis demonstrated that sole delaminations or sole fibre fracture resulted Figure 13. Tensile stress-strain curves at different applied strains ε 0 for three regions of the damage zone in a 4mm laminate impacted at 14J (20) . © Elsevier.…”

Section: Stiffness Of Impact Damage Zones In Tensionmentioning

confidence: 99%

“…Figure 14. Averaged apparent compressive stress-strain curves of damage zones in 4mm laminates impacted at various energies (20) . © Elsevier.…”

Section: Stiffness Of Impact Damage Zones In Tensionmentioning

confidence: 99%

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Modelling of impact damage zones in composite laminates for strength after impact

Olsson¹

2012

Aeronaut. j. (1968)

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This paper reviews findings on the type, morphology and constitutive behaviour of impact damage zones during loading after impact and their effect on the laminate strength and stability. The paper is limited to tape prepreg based monolithic laminates, although some similarities exist with impact damage in textile based laminates. Damage zones have a complex geometry with several damage types, which results in an interaction and competition between different failure mechanisms, e.g. local and global buckling, compressive failure, and delamination growth. Hence, simplified damage models may provide incorrect predictions of the failure load and failure mechanisms after impact. The constitutive behaviour of damage zones has been studied experimentally in tension and compression using an inverse method, and the results have been compared with detailed FE models of a generic impact damage. The paper is concluded with a discussion on analytical and computational models to predict the resulting strength of impacted laminates.

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Section: Olsson Modelling Of Impact Damage Zones In Composite Laminatsupporting

confidence: 90%

Section: Stiffness Of Impact Damage Zones In Tensionmentioning

confidence: 99%

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Modelling of impact damage zones in composite laminates for strength after impact

Olsson¹

2012

Aeronaut. j. (1968)

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“…For clarity, the regions highlighted by the dotted regions in (a) were caused by two loose tows on the back surface and, as such, should be disregarded. The buckled shape of the test coupon agrees with other stereo digital image correlation work on carbon/epoxy coupons of the same geometry [31].…”

Section: Buckling Behavioursupporting

confidence: 83%

Image-enhanced modelling of residual compressive after impact strength in laminated composites

Bull

Spearing

Sinclair

2018

Composite Structures

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This study implements key mechanisms and parameters observed from the previous compression after impact (CAI) experimental studies into finite element models, to study their effects parametrically on residual compression strength. The mechanisms and parameters include: impact damage area, the role of intact interfaces within the overall damaged region (identified here as the "undamaged cone"), interlaminar toughness, and the extent of permanent out-of-plane deformation. The findings highlight that within the limits observed experimentally, in addition to the size of the damaged area, interlaminar toughness and the extent of permanent out-of-plane deformation strongly affect CAI strength (by up to ~100% for a given damage area), with toughness playing a more significant influence than permanent out-of-plane deformation. For the first time, and contrary to much of the literature, the significant role of the undamaged cone is evidenced and quantified.

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“…The capability of the FE model to capture permanent indentation is attributed to the nonlinear shear formulation of the intralaminar damage model. This deformation may be significant in defining the compression-after-impact response of the laminates [35]. As discussed in the formulation of the damage model, shear strain was decomposed into elastic strain…”

Section: Global Impact Responsementioning

confidence: 99%

Predicting low velocity impact damage and Compression-After-Impact (CAI) behaviour of composite laminates

Tan

Falzon

Chiu

et al. 2015

Composites Part A: Applied Science and Manufacturing

396

245

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Low-velocity impact damage can drastically reduce the residual strength of a composite structure even when the damage is barely visible. The ability to computationally predict the extent of damage and Compression-After-Impact (CAI) strength of a composite structure can potentially lead to the exploration of a larger design space without incurring significant time and cost penalties. A high-fidelity three-dimensional composite damage model, to predict both low-velocity impact damage and CAI strength of composite laminates, has been developed and implemented as a user material subroutine in the commercial finite element package, ABAQUS/Explicit. The intralaminar damage model component accounts for physicallybased tensile and compressive failure mechanisms, of the fibres and matrix, when subjected to a threedimensional stress state. Cohesive behaviour was employed to model the interlaminar failure between plies with a bi-linear traction-separation law for capturing damage onset and subsequent damage evolution. The virtual tests set up in ABAQUS/Explicit were executed in three steps, one to capture the impact damage, the second to stabilize the specimen by imposing new boundary conditions required for compression testing and the third to predict the CAI strength. The observed intralaminar damage features, delamination damage area as well as residual strength are discussed. It is shown that the predicted results for impact damage and CAI strength correlated well with experimental testing without the need of model calibration which is often required with other damage models.

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Nonlinear compressive stiffness in impacted composite laminates determined by an inverse method

Cited by 37 publications

References 14 publications

Modelling of impact damage zones in composite laminates for strength after impact

Modelling of impact damage zones in composite laminates for strength after impact

Image-enhanced modelling of residual compressive after impact strength in laminated composites

Predicting low velocity impact damage and Compression-After-Impact (CAI) behaviour of composite laminates

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