Mechanistically based fatigue-damage evolution model for brittle matrix fibre-reinforced composites

Ramakrishnan, V.; Jayaraman, N.

doi:10.1007/bf00367835

Cited by 38 publications

(30 citation statements)

References 15 publications

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“…A comparison of damage curves for (0/90), (0/45) and (0/30) laminate systems (see Figs. 5,6,7,8 and 9) verified that the higher angle θ°in FRP (0/θ) composite laminates resulted in more damaging θ plies. It was also reported [16] that as the angle θ°increases, individual plies of a laminate show less constraint against the cracks growing between the plies of 0 and θ.…”

Section: (0/45) and (0/30) Frp Composite Laminatessupporting

confidence: 62%

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A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

Shirazi

Varvani‐Farahani

2009

Appl Compos Mater

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The present study develops a stiffness reduction-based model to characterize fatigue damage in unidirectional 0˚and θ°plies and (0/θ) laminates of fiber-reinforced polymer (FRP) composites. The proposed damage model was constructed based on (i) cracking mechanism and damage progress in matrix (Region I), matrix-fiber interface (Region II) and fiber (Region III) and (ii) corresponding stiffness reduction of unidirectional composite laminates as the number of cycles progresses. The proposed model enabled damage assessment of FRP (0/θ) composite laminates by integrating the fatigue damage values of 0˚and θ°plies. A weighting factor η was introduced to partition the efficiency of load carrying plies of 0°and θ°in the (0/θ) composite lamina. The fatigue damage curves of unidirectional FRP composite samples with off-axis angles of 0˚, 30˚, 45˚, and 90˚and composite laminate systems of (0˚/30˚), (0˚/45˚) and (0˚/90˚) predicted based on the proposed damage model were found in good agreement with experimental data reported at various cyclic stress levels and stress ratios in the literature.

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Section: (0/45) and (0/30) Frp Composite Laminatessupporting

confidence: 62%

“…The latter theory corresponds to the degradation of composite stiffness as fatigue cycles increase. Several researchers [1][2][3][4][5][6][7] have investigated fatigue damage response of unidirectional FRP composites based on reduction of composite stiffness as the number of fatigue cycles increased.…”

Section: Introductionmentioning

confidence: 99%

A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

Shirazi

Varvani‐Farahani

2009

Appl Compos Mater

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“…Die Schädigung von faserverstärkten Kunststoffen bei schwingender Beanspruchung wird üblicherweise durch Matrixrisse eingeleitet, gefolgt von Rißwachstum (,Crack-Bridging' oder ,Faser-Matrix-Debonding', abhän-gig von der Faser-Matrix-Haftung 25) ) und schließlich dem Faserbruch, der zum Versagen des Verbundwerkstoffs führt 25,26) . Weiterhin ist bekannt 27) , …”

Section: Schwingende Beanspruchungunclassified

Zum Verhalten von Jute- und Flachsfaser-Epoxidharz-Verbunden mit alkalibehandelten Fasern bei Feuchteexposition

Gassan

Błędzki

1999

Angew. Makromol. Chem.

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Es wurden Untersuchungen zum Einfluß einer Wasserlagerung auf die physikalischen Eigenschaften von Jute‐ und Flachsfasern und deren Verbunde mit einem Epoxidharz (EP) durchgeführt, wobei die verwendeten Jute‐ und Flachsfasern einer isometrischen Alkalibehandlung unterzogen worden waren. Für Jutefasern wurde ein stark anisotropes Quellverhalten festgestellt, welches durch die Alkalisierung noch verstärkt wurde. Jutefasern wiesen eine deutlich niedrigere Naßbruchkraft auf, für die Flachsfasern lag die Trockenbruchkraft etwa auf dem Niveau der Naßbruchkraft. Die Jute‐EP‐Verbunde wiesen, unabhängig von der Faserbehandlung, eine deutliche Abnahme der Zugfestigkeit nach einer 23tägigen Wasserlagerung auf, hingegen lagen die Werte der Flachs‐EP‐Verbunde sogar geringfügig über denen von nicht wassergelagerten Referenzen. Die dynamischen Verbundfestigkeiten der alkalibehandelten EP‐Verbunde lagen jeweils deutlich höher als die der unbehandelten Referenzen. Durch eine 49tägige Wasserlagerung wurden unterschiedlich deutliche Abnahmen der dynamischen Festigkeit in Abhängigkeit von Fasertyp und ‐behandlung ermittelt.

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“…In the present study, a stiffness degradation fatigue damage model is further extended based on an earlier developed damage model [9][10][11] …”

mentioning

confidence: 99%

Damage Assessment of CFRP [90/±45/0] Composite Laminates over Fatigue Cycles

2011

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The present paper develops a stiffness-based model to characterize the progressive fatigue damage in quasi-isotropic carbon fiber reinforced polymer (CFRP) [90/±45/0] composite laminates with various stacking sequences. The damage model is constructed based on (i) cracking mechanism and damage progress in matrix (Region I), matrix-fiber interface (Region II) and fiber (Region III) and (ii) corresponding stiffness reduction of unidirectional plies of 90°, 0°and angle-ply laminates of ±45°as the number of cycles progresses. The proposed model accumulates damages of constituent plies constructing [90/±45/0] laminates by means of weighting factor η 90 , η 0 and η 45 . These weighting factors were defined based on the damage progress over fatigue cycles within the plies 90°, 0°and ±45°of the composite laminates. Damage model has been verified using CFRP [90/±45/0] laminates samples made of graphite/epoxy 3501-6/AS4. Experimental fatigue damage data of [90/±45/0] composite laminates have fell between the predicted damage curves of 0°, 90°plies and ±45°, 0/±45°laminates over life cycles at various stress levels. Predicted damage results for CFRP [90/±45/0] laminates showed good agreement with experimental data. Effect of stacking sequence on the model of stiffness reduction has been assessed and it showed that proposed fatigue damage model successfully recognizes the changes in mechanism of fatigue damage development in quasi-isotropic composite laminates.

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Mechanistically based fatigue-damage evolution model for brittle matrix fibre-reinforced composites

Cited by 38 publications

References 15 publications

A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

A Stiffness Degradation Based Fatigue Damage Model for FRP Composites of (0/θ) Laminate Systems

Zum Verhalten von Jute- und Flachsfaser-Epoxidharz-Verbunden mit alkalibehandelten Fasern bei Feuchteexposition

Damage Assessment of CFRP [90/±45/0] Composite Laminates over Fatigue Cycles

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