A progressive fatigue damage model for composite structures in hygrothermal environments

Shan, Meijuan; Zhao, Libin; Hong, Haiming; Liu, Fengrui; Zhang, Jianyu

doi:10.1016/j.ijfatigue.2018.02.019

Cited by 47 publications

(14 citation statements)

References 46 publications

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“…

T^{*} goodbreak= \frac{T_{g} - T_{opr}}{T_{g} - T_{rm}}

where T g is the glass transition temperature of composite, T opr is the operation temperature, and T rm is the room temperature. A united model 68 as shown in Equation (17) is adopted here to quantitatively characterize the effect of temperature on the material property.

\begin{matrix} centertrue \\ \frac{E_{11}^{temp}}{E_{11}^{0}} = {((), T^{*})}^{a} & \frac{E_{22}^{temp}}{E_{22}^{0}} = {((), T^{*})}^{b} & \frac{G_{12}^{temp}}{G_{12}^{0}} = {((), T^{*})}^{c} \\ \frac{X_{T}^{temp}}{X_{T}^{0}} = {((), T^{*})}^{d} & \frac{X_{C}^{temp}}{X_{C}^{0}} = {((), T^{*})}^{e} & \frac{Y_{T}^{temp}}{Y_{T}^{0}} = {((), T^{*})}^{f} \\ \frac{Y_{C}^{temp}}{Y_{C}^{0}} = {((), T^{*})}^{g} & \frac{S_{12}^{temp}}{S_{12}^{0}} = {((), T^{*})}^{h} & \frac{ν_{12}^{temp}}{ν_{12}^{0}} = 1 \end{matrix}

where X T , X C , Y T , Y C , and S 12 are the longitudinal tensile and compressive, transverse tensile and compressive, and in‐planar shear strengths, respectively.…”

Section: Numerical Simulation On the Mode I Delamination Growthmentioning

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

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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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“…

T^{*} goodbreak= \frac{T_{g} - T_{opr}}{T_{g} - T_{rm}}

\begin{matrix} centertrue \\ \frac{E_{11}^{temp}}{E_{11}^{0}} = {((), T^{*})}^{a} & \frac{E_{22}^{temp}}{E_{22}^{0}} = {((), T^{*})}^{b} & \frac{G_{12}^{temp}}{G_{12}^{0}} = {((), T^{*})}^{c} \\ \frac{X_{T}^{temp}}{X_{T}^{0}} = {((), T^{*})}^{d} & \frac{X_{C}^{temp}}{X_{C}^{0}} = {((), T^{*})}^{e} & \frac{Y_{T}^{temp}}{Y_{T}^{0}} = {((), T^{*})}^{f} \\ \frac{Y_{C}^{temp}}{Y_{C}^{0}} = {((), T^{*})}^{g} & \frac{S_{12}^{temp}}{S_{12}^{0}} = {((), T^{*})}^{h} & \frac{ν_{12}^{temp}}{ν_{12}^{0}} = 1 \end{matrix}

where X T , X C , Y T , Y C , and S 12 are the longitudinal tensile and compressive, transverse tensile and compressive, and in‐planar shear strengths, respectively.…”

Section: Numerical Simulation On the Mode I Delamination Growthmentioning

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

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“…As mentioned before, results of the cycle counting are essential not only for identification of the stress histogram contents but also for determination of the fatigue strengths for arbitrary values of the stress ratios R. In more specific words, the cycle counting is vital for establishments of the Ω(R σ , σ m , σ u ) of Equation (17) and ξ σ i and ξ τ ij of Equation (20), for each half cycle. Substituting the obtained information in Equation (17) or (19) of the damage-based criterion the or Equation (36) or (37) of the equivalent stress approach gives the cycles to fatigue (N f ) predicted by the two fatigue criteria pertaining to fibre or matrix damages. The whole fatigue life may be determined based on Miner's damage accumulation rule.…”

Section: Postprocessing For Fatigue Life Assessment Purposesmentioning

confidence: 99%

“…Depending on the nature and details of the resulting histograms of the three-dimensional (3D) stress field, the indications of the global failure of the composite component may appear in the form of each of the mentioned failure modes. [14][15][16][17] Some other researchers have utilized progressive damage 18,19 or residual strength concepts. Because of the mentioned complexities, the available fatigue criteria on the composite components are still preliminary and limited ones.…”

Section: Introductionmentioning

confidence: 99%

“…Some authors have employed micromechanics damage mechanics concepts. [14][15][16][17] Some other researchers have utilized progressive damage 18,19 or residual strength concepts. A stiffness degradation multiaxial fatigue life assessment model was presented by Fujii et al 20 Cheng 21 used a residual strength degradation model for the life determination and the residual strength concept for the accumulation of fatigue damage of the composites.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Generalized 3D high cycle fatigue criteria for multiscale bridging‐based progressive damage analysis of multilayer composite parts under random loads and material deterioration

Shariyat

Rahimi‐Ghozat

2019

Fatigue Fract Eng Mat Struct

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Two frameworks are employed to develop two distinct categories of multiaxial high cycle fatigue life assessment models for composite components experiencing general and random loading conditions. In this regard, the decay in the material properties with cycles is also taken into account. It is obvious that in multilayer components, the fatigue failure is a progressive process that may be accompanied by gradual or sudden changes in the material properties and, consequently, the resulting stresses. In addition to using the traditional progressive damage analyses, a new concept is proposed for tracing of the localized fatigue failures more accurately. It is postulated that generally, the stress components have distinct frequencies, phase shifts, and mean values that all vary with time in a random manner. The proposed fatigue criteria, especially, the equivalent-stress-based ones, are capable of predicting various fatigue failure modes, such as the fibre breakage, matrix cracking, and interfacial debonding. A special and comprehensive fatigue failure tracking and cycle counting algorithms that are capable of handling the mentioned general peculiarities are proposed. The proposed HCF criteria and the relevant fatigue life assessment algorithm are then implemented on a composite multilayer monoleaf spring of a realistic vehicle under a random field-measured loading condition, as a typical component, and the results are compared and the experimental results conducted by the authors, for accuracy investigations. The considered stochastic road inputs have been chosen on the basis of the consumption times and field measurements. K E Y W O R D Scomposite mono-leaf spring, deterioration of the material, experimental results, new 3D HCF criteria, progressive fatigue-damage, realistic random load inputs

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“…Knowledge on dissipative processes -main factors responsible for development of damages, enables better use of materials' strength composing structure transferring the loads [2]. Anisotropy of fibrous laminates causes the orientation of cracks and their development depends not only on the load, geometry and boundary conditions, but also on the material's morphology [3]. In order composites to maintain the highest possible damage tolerance, their damage cannot occur in a catastrophic way and should consider the largest possible volume [2] of the loaded structure.…”

Section: Introductionmentioning

confidence: 99%

Initiation and Tolerance of Macro-Damage of First Ply (FBF) in a Process of Damaging of Hybrid Multi-Ply Structures Due to Reinforcement Archtecture

Pieniak

2018

Advances in Materials Science

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The objective of this paper was study and analysis of damaging process of multi-ply structure applied in dentistry. The aim was to analyze and experimentally evaluate tolerance of macro-damage of first ply (FPF - first ply failure) of multi-ply composite. A studied structure of composite makes a carrying structure for dental applications e.g. adhesive bridges. Influence of reinforcement structure on the residual carrying capacity of the studied multi-ply materials has been demonstrated. It has been shown that the type of fiber and fiber ribbon architecture play a major role in strength of studied reinforcements. Structures included in the study differ by the moment of macro-damage occurrence, carrying capacity and residual stiffness.

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A progressive fatigue damage model for composite structures in hygrothermal environments

Cited by 47 publications

References 46 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

Generalized 3D high cycle fatigue criteria for multiscale bridging‐based progressive damage analysis of multilayer composite parts under random loads and material deterioration

Initiation and Tolerance of Macro-Damage of First Ply (FBF) in a Process of Damaging of Hybrid Multi-Ply Structures Due to Reinforcement Archtecture

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