Progressive fatigue damage simulation method for composites

Nikishkov, Yuri; Makeev, Andrew; Seon, Guillaume

doi:10.1016/j.ijfatigue.2012.11.005

Cited by 60 publications

(39 citation statements)

References 31 publications

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“…Accurate stress-strain curves, strength, and modulus data are generated for multiple glass/epoxy and carbon/epoxy materials [4][5][6]. And third, the test method is viable for measurement of stress-strain relations at various load rates including static, fatigue [7][8][9], and impact load conditions. The most recent results verified simplicity of the SBS test based constitutive property approximations at impact load rates.…”

Section: Materials Characterizationmentioning

confidence: 99%

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Fatigue Life Assessment for Composite Structure

Makeev

Nikishkov

2011

ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives

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Abstract. This work presents some of the most recent advances in the technologies which could enable accurate assessment of useful life for composite aircraft fatigue-critical, flight-critical components and structure. Such technology advances include: (1) nondestructive subsurface measurement shift from just detection of defects to three-dimensional measurement of defect location and size; (2) material characterization methods ability to generate 3D material allowables at minimum time and cost; and (3) fatigue structural analysis techniques ability to capture multiple damage modes and their interaction. The authors summarize their recent results in all three subjects. BackgroundCurrently, composite designs adopt metal design philosophy and use the same factor of safety of 1.5 to determine the ultimate design load from the limit load even though composite parts are inherently more susceptible to variations in manufacturing processes than metal parts. In addition to material variation in the resin content, bulk factor, and fiber alignment, part fabrication process variations such as operator skill, tooling setup, humidity fluctuation, equipment control, etc. are common causes that contribute to variation in part quality. Consequently, the increased sensitivity of composite part quality to material and process variations lowers production yields. In order to increase production yields, heavy burden is placed on composite manufacturing communities to understand and control their processes. Production yields of greater than 90% remain a "hit-and-miss" target.The effects of manufacturing process parameters on structural strength, durability and damage tolerance are not well understood. In particular, the effects of inadequate design method and manufacturing process used to produce carbon/epoxy and glass/epoxy composite aircraft fatigue-critical, flight-critical components manifest themselves as defects such as wrinkles and porosity/voids, and such defects impact the performance and the service life of these components.Manufacturing defects can severely deteriorate the matrix-dominated properties resulting in degraded strength and fatigue structural performance of composites. * Oral presentation.

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Section: Materials Characterizationmentioning

confidence: 99%

“…Figure 11 shows measured and predicted fatigue delamination patterns for article 1 at the specified number of cycles. Explicit modeling of plyterminations present in the +45-degree ply-groups at the failure-critical locations was required to capture the ply-interface damage locations [8].…”

Section: 3mentioning

confidence: 99%

Fatigue Life Assessment for Composite Structure

Makeev

Nikishkov

2011

ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives

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“…Nikishkov et al [9] have introduced progressive simulation methods for unidirectional IM7/8552 composites, describing modeling methodologies to simulate the delamination, matrix damage onset and progression under fatigue loads. Similar fatigue damage studies using a phenomenological approach can be found in References [10][11] based on progressive fatigue damage accumulation.…”

Section: Introductionmentioning

confidence: 99%

A 3D progressive damage model for fatigue analysis of woven fabric composites

Chinh¹

2018

Preprint

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A new 3D damage model is developed to predict the progressive failure and accumulated fatigue damage of woven fabric composite materials. Stress-based failure criteria are used to predict the damage initiation in x-tow, y-tow, and matrix constituent. An S-N based damage accumulation model is implemented to characterize the cycle dependent strength of the xand y-fiber tows and matrix subjected to axial tension, compression, or in-plane share loading. A curve-fit non-linear shear model is also employed based on the static coupon test data of (+45/-45) woven fabric laminates. A static failure progression module is used to predict the damage and failure at the peak load prior to fatigue cycling. Stiffness degradation, fatigue damage accumulation, and failure mode detection are performed during the fatigue marching process. The developed user-defined material model for Abaqus features: 1) description of initial nonlinear shear before the damage initiation; 2) characterization of failure initiation based on a maximum stress criterion; and 3) performance of fatigue damage accumulation using a phenomenological model based on S-N test data. The predictive capabilities of the developed model are demonstrated using tensiontension fatigue of SYNCOGLAS R420 E-glass woven fabrics.

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“…The joint is the spaced welding structure and therefore, it is very concerned with the fatigue performance. Scholars have done a lot of work in the field of fatigue cumulative damage, and put forward some calculation models and fatigue cumulative damage rules, such as linearity fatigue cumulative damage theory [11], bilinear fatigue cumulative damage theory [12], non-linear fatigue cumulative damage theory [13], probability fatigue cumulative damage theory [14] and so on. At present, the fatigue problem is investigated with FEM and model test.…”

Section: Introductionmentioning

confidence: 99%

Finite element modelling for SCFs in steel tubular T-joints with concrete-filled chords under axial loading in the brace

Wang¹,

Qin²

2014

Life-Cycle of Structural Systems

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The fatigue performance of steel truss integral joint is analyzed based on multi-scale FEM. Numerical results are verified with experimental ones. The fatigue performance of steel truss integral joint is analyzed using a sea-crossing suspension bridge as its background. The 1:2 scale model fatigue test is taken. After 2e6 time load loops, the stress situation of integral joint is stable and fatigue performance is satisfactory for requirements. The multi-scale FEM, whose main researching part adopts three-dimensional elements while the connecting component adopts the common beam element, can reduce the computational cost. The connection elements are used to connect the beam elements and threedimensional elements. The connection element has two joints, one of which has six degrees of freedom, three translation degrees of freedom and three rotational degrees of freedom, all degrees of freedom being coupled. The multi-scale FEM and the experimental one yield very close results The multi-scale FEM can provide an accurate simulation of the main research part and ensure the fatigue life forecast so as to simplify the calculation. This method is high efficient and feasible. The multi-scale FEM provides a new and reliable method for the fatigue performance of structure analysis.

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Progressive fatigue damage simulation method for composites

Cited by 60 publications

References 31 publications

Fatigue Life Assessment for Composite Structure

Fatigue Life Assessment for Composite Structure

A 3D progressive damage model for fatigue analysis of woven fabric composites

Finite element modelling for SCFs in steel tubular T-joints with concrete-filled chords under axial loading in the brace

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