High-temperature fatigue behaviour of notched quasi-isotropic thermoplastic and thermoset laminates: Influence of matrix ductility on damage mechanisms and stress distribution

Vieille, B.; Albouy, W.; Bouscarrat, D.; Taleb, Lakhdar

doi:10.1016/j.compstruct.2016.06.015

Cited by 20 publications

(30 citation statements)

References 22 publications

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“…As it delays matrix cracking and slows down inter-and intralaminar crack propagation during fatigue loading, the specific roles of both matrix ductility and toughness [34] should also be observed in TP-based laminates subjected to an impact scenario at a service temperature higher than Tg. Indeed, in addition to the limited propagation of delamination due to the intrinsic toughness of woven-ply laminates [7], temperature has also a nonnegligible effect: matrix is tougher and more ductile at high temperature T > Tg what leads to local plastic deformation in matrixrich region of the laminates before damage appears, resulting in slowing down matrix cracking.…”

Section: Impact Behaviormentioning

confidence: 99%

Influence of temperature on the impact behavior and damage tolerance of hybrid woven-ply thermoplastic laminates for aeronautical applications

Dubary

Taconet

Bouvet

et al. 2017

Composite Structures

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Impact damage tolerance of hybrid carbon and glass fibers woven-ply reinforced PolyEther Ether Ketone (PEEK) thermoplastic (TP) laminates obtained by consolidation process is investigated. Service temperature being one of the most important parameters to screen TP or thermosetting matrix for aeronautical purposes, impact testing at room temperature (RT) and near the glass transition temperature (Tg) has been conducted. From the results, it turns out that temperature has little influence on the impact behavior in terms of maximum force developed or maximum deflection, though it reduces the dissipated energy especially at lower impact energy. However, temperature has a strong effect on the internal and external damages caused to the plate, as it increases the permanent indentation and it limits the projected delaminated area. As for the influence of temperature on the compressive residual strength of the laminates, it also appears that the classical experimental setup for CAI tests is not completely appropriate to draw a clear cut conclusion. At last the obtained results show that the considered TP-based laminates are characterized by a very good impact behavior and a high-degree of damage tolerance.

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Section: Impact Behaviormentioning

confidence: 99%

Influence of temperature on the impact behavior and damage tolerance of hybrid woven-ply thermoplastic laminates for aeronautical applications

Dubary

Taconet

Bouvet

et al. 2017

Composite Structures

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“…The studied composite materials are carbon fabric reinforced laminates consisting of a semicrystalline high‐performance PPS supplied by the Ticona company . The woven‐ply prepreg, supplied by SOFICAR, consists of 5‐harness satin weave carbon fiber fabrics (T300 3K 5HS) whose volume fraction is 50%.…”

Section: Materials and Experimentalmentioning

confidence: 99%

“…The glass transition temperature of the C/PPS laminates studied in this work is about 107°C . Three specimens were tested in each configuration.…”

Section: Materials and Experimentalmentioning

confidence: 99%

“…), especially in wide plates . It appears that woven‐ply laminates are characterized by matrix‐rich regions at the crimps (where warp fiber bundles undulate over weft fiber bundles), and the potential benefit of these matrix‐rich regions is the development of plastic yield zones at the cracks tip as intraply and interply cracks propagate . Depending on matrix toughness, the localized matrix plasticization is instrumental in ruling damage mechanism, as these matrix‐rich regions may act as cracks barriers and subsequent propagation in unnotched laminates, as well as in notched laminates .…”

Section: Introductionmentioning

confidence: 99%

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Evolution of the strain energy release rate during ductile or brittle failure in woven‐ply reinforced thermoplastic laminates under high temperature conditions

Vieille

2017

Polymer Composites

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Depending on laminates' stacking sequence, the contribution of matrix behavior to the strain energy release rate is evaluated during failure in brittle and ductile composite laminates subjected to high temperature conditions (T > T g ) when matrix toughness is enhanced. The purpose of this work is therefore to investigate the strain energy released along with crack growth in 5harness satin weave carbon fabric reinforced polyphenylene sulfide (PPS) structures with a Single Edge Notch. The crack growth appears to be self-similar in quasi-isotropic (QI) laminates, and nonself-similar in angle-ply (AP) laminates. Based on fracture mechanics concepts, semianalytical representations of the translaminar failure are combined with an Acoustic Emission (AE) technique to correlate the cumulative AE energy to the strain energy release rate. The experimental results reveal that the fracture toughness increases with increasing precrack length in QI laminates, whereas the effect of increase in precrack length exhibits reduced fracture toughness in AP laminates. The energy released during a non-self-similar crack growth is all the more significant than the stress concentration factor is reduced. A small defect (e.g., precrack) means a larger portion of the mechanical energy brought to the specimen to be dissipated during failure by means of large plastic deformations. With respect to QI laminates, the contribution of PPS matrix toughness to the fracture energy released is more significant in highly ductile AP laminates, resulting in higher fracture toughness. POLYM. COMPOS., 00:000-000,

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“…When the temperature reaches glass‐transition temperature ( T g ) or exceeds it, the matrix becomes soft or even degrades. Moreover, due to the differences of thermal expansion coefficient between fiber and resin matrix, the interfaces are more vulnerable to stress concentration or relaxation of thermal stress under high temperature, diminishing the composite's performance . Civil aviation aircraft generally fly at an altitude of more than 8000 m, located at the bottom of the stratosphere, with a perennial temperature of −56.5 °C.…”

Section: Introductionmentioning

confidence: 99%

Temperature effects on structural integrity of fiber‐reinforced polymer matrix composites: A review

Pei

Han

Ding

et al. 2019

J of Applied Polymer Sci

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Fiber‐reinforced polymer matrix composites (FRPMCs) are the most promising and valuable material developed in the last few decades. In response to the increased research and publications concerning the thermal stability of FRPMCs, this review has culled typical journals for publications relevant to structural stability. In this review, the effects of temperature on the structural integrity of FRPMCs are discussed from the perspective of matrix types, fiber types, nanoparticle (NP) modifications on resin matrix, and various related mechanical properties. For NP‐modified FRPMCs, characterization of all anisotropic properties under various strain rates and temperatures becomes essential for analysis, design, and numerical simulations. Improving the structural stability of FRPMCs at different temperatures is an important direction. © 2019 Wiley Periodicals, Inc. J. Appl. Polym. Sci. 2019, 136, 48206.

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High-temperature fatigue behaviour of notched quasi-isotropic thermoplastic and thermoset laminates: Influence of matrix ductility on damage mechanisms and stress distribution

Cited by 20 publications

References 22 publications

Influence of temperature on the impact behavior and damage tolerance of hybrid woven-ply thermoplastic laminates for aeronautical applications

Influence of temperature on the impact behavior and damage tolerance of hybrid woven-ply thermoplastic laminates for aeronautical applications

Evolution of the strain energy release rate during ductile or brittle failure in woven‐ply reinforced thermoplastic laminates under high temperature conditions

Temperature effects on structural integrity of fiber‐reinforced polymer matrix composites: A review

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