A new model characterizing the fatigue delamination growth in DCB laminates with combined effects of fiber bridging and stress ratio

Jiang, Linfei; Zhang, Yongxiang; Gong, Yu; Li, Wangchang; Ren, Shangjie; Liu, Hao

doi:10.1016/j.compstruct.2021.113943

Cited by 8 publications

(5 citation statements)

References 42 publications

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“…During the mode I delamination growth process, the fibers pulled out from the matrix bridge the fracture surfaces and enforce a closing force on the fracture surface 62,63 . The mechanical behavior of bridging fibers can be described by the bridging law, which relates the bridging stress σ with the crack opening displacement (COD) δ .…”

Section: Experimental Results Of Dcb Tests At Different Temperaturesmentioning

confidence: 99%

“…During the mode I delamination growth process, the fibers pulled out from the matrix bridge the fracture surfaces and enforce a closing force on the fracture surface. 62,63 The mechanical behavior of bridging fibers can be described by the bridging law, which relates the bridging stress σ with the crack opening displacement (COD) δ. As shown in Figure 8, in the bridging zone close to the crack tip, the density of bridging fibers is higher with short lengths and a higher bridging stress exhibits.…”

Section: Bridging Lawmentioning

confidence: 99%

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Temperature effect on the static mode I delamination behavior of aerospace‐grade composite laminates: Experimental and numerical study

Gong

Jiang

et al. 2022

Fatigue Fract Eng Mat Struct

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Aerospace structures are exposed to high‐temperature conditions during service. In‐depth study for the temperature effect on composite interlaminar properties is important for the structural design and reliable application. In this study, mode I delamination behaviors at different temperatures are investigated, to understand the effects of temperature on the delamination growth process, including fracture toughness, bridging stress, and failure mechanism. It is found that R‐curve behavior presents at all temperatures. The initial and steady‐state fracture toughnesses exhibit linear increase trends with the increase of the temperature, from which equations are established to predict the initial and steady‐state fracture toughnesses at other temperatures. More bridging fibers are observed at higher temperatures, and the resulted fracture resistance at 130°C is 136.9% higher than that at room temperature. The maximum bridging stress also increases with the increase of temperature. A numerical framework based on the cohesive zone model is established for delamination modeling. Material parameters at various temperatures are obtained by an exponential model. Suitable values of interfacial parameters in cohesive elements are numerically determined. Predicted load–displacement responses agree well with the experimental ones, illustrating the applicability of the proposed numerical method.

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Section: Experimental Results Of Dcb Tests At Different Temperaturesmentioning

confidence: 99%

Section: Bridging Lawmentioning

confidence: 99%

Temperature effect on the static mode I delamination behavior of aerospace‐grade composite laminates: Experimental and numerical study

Gong

Jiang

et al. 2022

Fatigue Fract Eng Mat Struct

Self Cite

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“…In fact, the model which considers the fiber bridges proposed in references [76,101,104] also take the effect of the load ratio into account. In addition to replacing similar parameters with √ G max − √ G min 2 , the coefficient of the Paris law (C (a, R)) is set as a function of fatigue crack length (a) and load ratio (R).…”

Section: Load Ratio-modified Modelmentioning

confidence: 99%

Review and Assessment of Fatigue Delamination Damage of Laminated Composite Structures

Deng,

Zhou,

et al. 2023

Materials

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Fatigue delamination damage is one of the most important fatigue failure modes for laminated composite structures. However, there are still many challenging problems in the development of the theoretical framework, mathematical/physical models, and numerical simulation of fatigue delamination. What is more, it is essential to establish a systematic classification of these methods and models. This article reviews the experimental phenomena of delamination onset and propagation under fatigue loading. The authors reviewed the commonly used phenomenological models for laminated composite structures. The research methods, general modeling formulas, and development prospects of phenomenological models were presented in detail. Based on the analysis of finite element models (FEMs) for laminated composite structures, several simulation methods for fatigue delamination damage models (FDDMs) were carefully classified. Then, the whole procedure, range of applications, capability assessment, and advantages and limitations of the models, which were based on four types of theoretical frameworks, were also discussed in detail. The theoretical frameworks include the strength theory model (SM), fracture mechanics model (FM), damage mechanics model (DM), and hybrid model (HM). To the best of the authors’ knowledge, the FDDM based on the modified Paris law within the framework of hybrid fracture and damage mechanics is the most effective method so far. However, it is difficult for the traditional FDDM to solve the problem of the spatial delamination of complex structures. In addition, the balance between the cost of acquiring the model and the computational efficiency of the model is also critical. Therefore, several potential research directions, such as the extended finite element method (XFEM), isogeometric analysis (IGA), phase-field model (PFM), artificial intelligence algorithm, and higher-order deformation theory (HODT), have been presented in the conclusions. Through validation by investigators, these research directions have the ability to overcome the challenging technical issues in the fatigue delamination prediction of laminated composite structures.

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“…In fact, the model which is considering fiber bridging proposed by [60,85,88] also take the effect of loading ratio into account. In addition to replacing similar parameters with   2 max min GG  , the coefficient of Paris Law C (a, R) is set as a function of the fatigue crack length a and the loading ratio R. However, m(R) only depends on loading ratio R. By this way, the fatigue crack growth curves under different loading ratios are unified under the influence of fiber bridge.…”

Section: Loading Ratio Modified Modelmentioning

confidence: 99%

Review and Assessment on Fatigue Delamination Damage of Laminated Composite Structures

Deng,

Zhou,

et al. 2023

Preprint

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The fatigue delamination damage is one of the most important fatigue failure modes of laminated composite structures. However, the developments of the theoretical framework, mathematical/physical model and numerical simulation of fatigue delamination are still challenging issues, and there is a lack of systematic classification. This article reviews the experimental phenomena of the onset and propagation stage of delamination under fatigue loading, and summarizes the commonly used phenomenological models for laminated composite structures. The research methods, general modeling formulas and development prospects of the phenomenological models are presented in detail. In the light of the analysis of finite element model (FEM) for the laminated composite structures, a number of simulation methods of fatigue delamination crack propagation damage model are carefully classified. Furthermore, within the theoretical framework of strength theory model (SM), fracture mechanics model (FM), damage mechanics model (DM) and hybrid model (HM), the complete procedure, application, capability assessment, advantages and limitations of the models are also discussed in detail. Finally, several valuable suggestions are given for the research interests, and challenging technical problems that need to be overcome on the fatigue delamination prediction of laminated composite structures in the future.

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A new model characterizing the fatigue delamination growth in DCB laminates with combined effects of fiber bridging and stress ratio

Cited by 8 publications

References 42 publications

Temperature effect on the static mode I delamination behavior of aerospace‐grade composite laminates: Experimental and numerical study

Temperature effect on the static mode I delamination behavior of aerospace‐grade composite laminates: Experimental and numerical study

Review and Assessment of Fatigue Delamination Damage of Laminated Composite Structures

Review and Assessment on Fatigue Delamination Damage of Laminated Composite Structures

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