Fatigue-driven failure criterion for progressive damage modelling and fatigue life prediction of composite structures

Xiong, Jun-Jiang; Zhu, Yun-Tao; Luo, Chuyang; Li, Yusheng

doi:10.1016/j.ijfatigue.2020.106110

Cited by 23 publications

(12 citation statements)

References 30 publications

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“…(10). Material constants (listed in Table 5) for fatigue-induced residual strength model are estimated from axial constant amplitude fatigue tests [41] of plain-weave 3238A/EW250F laminates [(0/90)] 9 and [(45/-45)] 9 by using the fitting method presented in Appendix C. The left side of laminate is fully fixed and fatigue load is applied on the right surface in pressure. The top and bottom sides of laminate are constrained to model the boundary constraint of anti-buckling device in the compression-dominated fatigue cycles (see Fig.…”

Section: Pif Progressive Damage Analysismentioning

confidence: 99%

Progressive damage modelling and fatigue life prediction of Plain-weave composite laminates with Low-velocity impact damage

Cheng

Tan

Xiong

2021

Composite Structures

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Section: Pif Progressive Damage Analysismentioning

confidence: 99%

Progressive damage modelling and fatigue life prediction of Plain-weave composite laminates with Low-velocity impact damage

Cheng

Tan

Xiong

2021

Composite Structures

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“…Typical aeronautical composite stiffened panels can operate in the post-buckling regime, but it's hard to foresee how they'll fail. This is because it is difficult to forecast their mechanism of collapse because the post-buckling deformation interacts with many failure modes like intralaminar damage, delamination, and skin-stringer separation [12]. Fatigue loading conditions further complicate the phenomenon due to interactions between geometric nonlinearities of the response, different damage modes, and the accumulation of cyclic damage.…”

Section: Introductionmentioning

confidence: 99%

Determination of the fatigue behavior of the composite Single-Stringer structure based on the quasi-static method

Shomran

Faisal

Hussein

et al. 2023

EEJET

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In this investigation, the Mechanical Behavior of the composite Single-Stringer structure was subjected to numerical analysis in order to better understand its properties. As the primary material for the modeling process, the carbon-epoxy IM7/8552 with quasi-isotropic Layups has been utilized. The outcomes of the numerical analysis that were carried out on the structure while it was in its static state have been put into the structural tool that was developed by the ANSYS programme. The fundamental boundary conditions have been defined on the basis of the information that was received from the testing. Static forces with a combined magnitude of 13.7 kN are being applied to the composite Single-Stringer structure. Shear stresses, direction deformation, von mises stresses, and total deformation have all been shown to have an effect on a material's mechanical behaviour, and this effect has been demonstrated. The calculations indicate that there is a maximum amount of bending that can take place as a direct result of the load that is being applied, and that amount is equal to 0.0147. The maximum amount of bending that can take place as a direct result of the load that is being applied is equal to 0.0147. As a consequence of the application of 13.7 kN of pressure, the von Mises stress, which is also frequently referred to as comparable stresses, has reached 51.9 MPa. Shear stresses have been estimated in three distinct plans, and it was discovered that the shear stress that was applied to the XY plane achieved a maximum of 15 MPa, but the shear stress that was applied to the XZ plane reached a maximum of 9.8 MPa. This was found. Both aeroplanes were put through precisely the same amount of tension at the exact same time. At this time, the shear stress on the plane YZ has reached a level of 1.5 MPa.

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“…Recently, the PFDM approach has been successfully applied to investigate the fatigue failure behaviors of composite heterostructures, including notched composite rings [17], full-scale composite cabin [18] and high-speed composite craft [19]. However, most of the above models employed a sudden-discount approach to degrade the properties once the failure criteria are activated, which is too empirical and may result in strong mesh dependency for numerical predictions [20,21].…”

Section: Introductionmentioning

confidence: 99%

A reliable progressive fatigue damage model for life prediction of composite laminates incorporating an adaptive cyclic jump algorithm

Zheng

Guo

Wang

et al. 2022

Composites Science and Technology

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Fatigue-driven failure criterion for progressive damage modelling and fatigue life prediction of composite structures

Cited by 23 publications

References 30 publications

Progressive damage modelling and fatigue life prediction of Plain-weave composite laminates with Low-velocity impact damage

Progressive damage modelling and fatigue life prediction of Plain-weave composite laminates with Low-velocity impact damage

Determination of the fatigue behavior of the composite Single-Stringer structure based on the quasi-static method

A reliable progressive fatigue damage model for life prediction of composite laminates incorporating an adaptive cyclic jump algorithm

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