Damage Propagation by Cyclic Loading in Drilled Carbon/Epoxy Plates

Durão, Luís Miguel P.; Matos, João E.; Loureiro, Nuno Calçada; Esteves, J. L.; Fernandes, Susana C. F.

doi:10.3390/ma16072688

Cited by 5 publications

(5 citation statements)

References 42 publications

(51 reference statements)

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“…The geometry of the specimens is presented in Figure 7. Defects induced during the machining of the hole can affect the load-bearing capacity of the laminate [63]. In the case studied here, small delaminations could be observed after machining.…”

Section: Methodsmentioning

confidence: 78%

Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates

Maneval,

Vedvik,

Echtermeyer

2023

J. Compos. Sci.

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The failure of composite laminates under cyclic fatigue loads is complex, as multiple failure mechanisms are in play at different scales and interact with each other. Predicting the remaining fatigue life as well as the residual capacities of a composite laminate or component is crucial, particularly for safety-critical applications. A progressive fatigue model is proposed to describe the catastrophic failure of open-hole laminates under tensile cyclic fatigue. To represent both intra-laminar and inter-laminar damage, a combination of a continuum damage mechanics model (CDM) and a discrete cohesive zone model (CZM) is implemented in the finite element (FE) software Abaqus. The CDM combines fibre- and matrix-dominated S-N curves with the Palmgren–Miner accumulation rule and Hashin’s residual strength to form a fatigue failure criterion differentiating between fibre failure (FF) and matrix failure (MF). The CZM implemented in this work is the CF20 model proposed by NASA. Fatigue cycling is simulated using an external cycle-jump scheme, where the stiffness degradation is conducted between the FE simulations outside of the implicit solver [90/0] s. Glass fibre reinforced polymer (GFRP) open-hole specimens were tested in tensile cyclic fatigue at a load ratio of 0.1. The experiments were reproduced numerically and the results compared. After calibration of a set of parameters based on one load level, the model was able to reproduce the experimental S-N curve very well, predicting a slope of −0.10, while the experimental value was −0.11. The failure sequence of the laminate was also successfully reproduced. The growth of the split from the hole, and its interaction with inter-laminar delamination, was successfully captured. The proposed approach was able to describe the fatigue failure of an open-hole laminate with a minimal set of material inputs using a simplified fatigue damage model while avoiding convergence issues.

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Section: Methodsmentioning

confidence: 78%

Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates

Maneval,

Vedvik,

Echtermeyer

2023

J. Compos. Sci.

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“…The complexity of the above issue, resulting from the possibility of designing the material properties of laminated composites, makes this topic still valid for researchers. The literature [ 23 , 24 , 25 , 26 ] offers solutions to the problem of hole formation in composite materials.…”

Section: Introductionmentioning

confidence: 99%

Failure Mechanism of Tensile CFRP Composite Plates with Variable Hole Diameter

Wysmulski

2023

Materials

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Real thin-walled composite structures such as aircraft or automotive structures are exposed to the development of various types of damage during operation. The effect of circular hole size on the strength of a thin-walled plate made of carbon fibre-reinforced polymer (CFRP) was investigated in this study. The test object was subjected to tensile testing to investigate the strength and cracking mechanism of the composite structure with variable diameter of the central hole. The study was performed using two independent test methods: experimental and numerical. With increasing diameter of the central hole, significant weakening of the composite plate was observed. The study showed qualitative and quantitative agreement between the experimental and numerical results. The results confirmed the agreement of the proposed FEM model with the experimental test. The novelty of this study is the use of the popular XFEM technique to describe the influence of the hole size on the cracking and failure of the composite structure. In addition, the study proposes a new method for determining the experimental and numerical damage and failure loads of a composite plate under tension.

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“…The complexity of the above issue resulting from the possibility of shaping the properties of laminated composites makes this research problem still valid. In the literature one can find studies [20][21][22] which propose solutions to the problem of hole formation in composite materials.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Study of Crack Propagation in the Tensile Composite Plate with the Open Hole

Wysmulski¹

2023

Adv. Sci. Technol. Res. J.

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In this study, the thin-walled plate with the central open hole made of carbon-epoxy composite was investigated. The plate was tested in tension to investigate the mechanism of crack formation in the composite structure. The studies were carried out using two individual methods: experimental and numerical. In the experiment test, load was measured as the function of plate elongation. The Plate elongation was analysed using the Aramis optical noncontact measurement system. In the numerical study, the FEM model reproducing the experimental conditions was developed in the Abaqus software. The cracking process was modelled using the XFEM method (extended finite element method). This procedure allowed the of the composite to be examined over the full range of the tensile load. The behaviour of the plate with a circular open hole was investigated before damage symptoms and the damage initiation load was determined. The study continued to analyse the initial cracking and delamination of the laminate layers, together with crack propagation leading to cracking of all the laminate layers (complete failure of the composite structure). The novelty of this study is that it uses the popular XFEM method to describe the cracking and failure of the composite structure. In addition, the study proposes the novel method for determining the crack initiation and failure loads of the composite plate under tension, and the results obtained thereby are verified numerically.

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Damage Propagation by Cyclic Loading in Drilled Carbon/Epoxy Plates

Cited by 5 publications

References 42 publications

Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates

Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates

Failure Mechanism of Tensile CFRP Composite Plates with Variable Hole Diameter

Numerical and Experimental Study of Crack Propagation in the Tensile Composite Plate with the Open Hole

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