ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Critical discussions on mode I fatigue delamination with large⁃scale fibre bridging in composite laminates
Received date: 2023-11-27
Revised date: 2024-02-21
Accepted date: 2024-05-23
Online published: 2024-05-31
Supported by
National Key Laboratory of Strength and Structural Integrity Science Foundation(ASSIKFJJ202302003);National Natural Science Foundation of China(12272110);Aeronautical Science Foundation of China(2022Z055077004)
Advanced carbon fibre reinforced polymer composites have been widely used in aerospace industry， because of their excellent mechanical properties and great weight-saving potential. Fatigue delamination has been demonstrated the main reason for the failure of composite structures in their long-term operations. Fiber bridging， as an important and unique shielding mechanism， has significant effects on fatigue delamination behavior. And it has been demonstrated that composite laminates have even lower mode I fatigue delamination resistance. As a result， it is really important to have thorough investigations on mode I fatigue delamination with large-scale fibre bridging in composite laminates， to guarantee the integrity of composite structures. This paper therefore provides critical reviews and discussions on the research work carried out by the author’s research group in this field in the past several years. And the main contents of this paper can be organized as following aspects： the effects of fibre bridging on fatigue delamination behavior， and bridging mechanism in fatigue delamination； the similarity for fatigue delamination with large-scale fibre bridging， and Paris type correlations for fibre-bridged mode I fatigue delamination characterization； the application and verification of the proposed Paris type correlations in fibre-bridged fatigue delamination interpretations. The results clearly demonstrated that the presence of fiber bridging has significant retardation effects on mode I fatigue delamination behavior. Particularly， fatigue delamination growth can decrease significantly with the development of fibre bridging， using the basic Paris law in fatigue data reduction. The mechanism of fiber bridging in fatigue delamination is different from that in static delamination in the perspective of energy dissipation. Particularly， fibre bridging has negligible contribution to permanent energy dissipation in fatigue delamination， unless there is failure in them. Bridging fibres in most cases only periodically store and release strain energy under cyclic loading， making the most energy dissipation still concentrate around the crack front （regardless of fibre bridging） in fatigue delamination. And the fractographic examinations on fatigue fracture surfaces indicate that the presence of fibre bridging indeed has little influence on the damage mechanism in mode I fatigue delamination. According to the energy dissipation and fractographic examinations， it is therefore reasonable to use the strain energy release rate that applied around the crack front as the similitude parameter to appropriately represent fatigue delamination behavior with significant fibre bridging at a given stress ratio， which can well obey the similitude principles. A two-parameter Paris type correlation was proposed to account for stress ratio. And the results clearly indicated that the use of this two-parameter model can appropriately determine fibre-bridged fatigue delamination behavior at different stress ratios and temperatures.
Liaojun YAO , Jingchao WEI , Xiangming CHEN , Mingyue CHUAI , Hanyue LI , Licheng GUO . Critical discussions on mode I fatigue delamination with large⁃scale fibre bridging in composite laminates[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(18) : 229919 -229919 . DOI: 10.7527/S1000-6893.2024.29919
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