Fatigue simulation for titanium/CFRP hybrid laminates using cohesive elements

Yamaguchi, T.; Okabe, Tomonaga; Yashiro, Shigeki

doi:10.1016/j.compscitech.2009.04.020

Cited by 33 publications

(13 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Burianek and Spearing found that the fatigue crack of Ti/CFRP FMLs initiated from the free edges and the area of stress concentration. According to Yamaguchi et al, the interfacial strength was a main factor in delamination and the crack propagation rate. Burianek et al predicted crack growth using the virtual crack closure technique (VCCT).…”

Section: Introductionmentioning

confidence: 99%

Fatigue crack growth and delamination mechanisms of Ti/CFRP fibre metal laminates at high temperatures

Jin

Chen

Luo

et al. 2020

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

Ti/CFRP (titanium/carbon fibre reinforced polymer) fibre metal laminates (FMLs) are composed of titanium sheets and carbon fibres reinforced PMR (polymerization of monomeric reactants) type polyimide resin. Due to the outstanding heat resistance of the material, it can be used in hypersonic aircraft applications. Fatigue cracks in the metal layer and delamination at metal/fibre interface may occur in long-term high-temperature use processes. However, the behaviour of the fatigue failure at high temperatures has not been investigated. A temperature-dependent equation has not been presented to predict the crack growth behaviour at high temperatures. In this study, to investigate the crack propagation and delamination behaviours, fatigue crack growth rate tests using tension-tension loads at 25 C, 80 C, 120 C, and 150 C were conducted in accordance with ASTM E647-15e1. The results indicated that the variation in fatigue crack growth rate could be described by a modified temperature-dependent Paris equation. Interfacial strength and tensile strength may influence fatigue failure at high temperatures. Hence, these strength values were also obtained to analyse the mechanism of fatigue behaviour. The delamination area increased exponentially with temperature due to the weakening of the Ti/CFRP interface, and delamination was invariably generated on the microcracks of the titanium layers. K E Y W O R D S delamination, fatigue crack growth, fibre metal laminates, thermal effect

show abstract

Section: Introductionmentioning

confidence: 99%

Fatigue crack growth and delamination mechanisms of Ti/CFRP fibre metal laminates at high temperatures

Jin

Chen

Luo

et al. 2020

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

show abstract

“…High‐strength titanium (Ti) alloys exhibit high specific strength, and when combined with carbon FRP (CFRP), they were also a suitable choice in previous studies . Most studies on fatigue in Ti‐alloy‐containing FML have focused on experimental and numerical investigations of the progress of fatigue damage using single‐edge and holed specimens during fatigue loading . However, a few studies have reported on the fatigue damage evolution processes of unnotched Ti‐alloy‐containing FML.…”

Section: Introductionmentioning

confidence: 99%

Effect of carbon fibres on the static and fatigue mechanical properties of fibre metal laminates

Naito

Shirasu

Tanaka

2020

Fatigue Fract Eng Mat Struct

View full text Add to dashboard Cite

It is crucial to understand the characteristic fatigue crack initiation and its growth mechanisms, as well as the relationship between the mechanical properties and the fatigue damage evolution in fibre metal laminates (FMLs). Two types of FML were studied in this work: a polyacrylonitrile-based carbon fibre epoxy matrix composite sandwiched by Ti-6Al-4V (Ti-alloy) sheets (IMS60-Ti) and a pitch-based carbon fibre epoxy matrix composite sandwiched by Ti-alloy sheets (K13D-Ti). The static and fatigue mechanical properties of IMS60-Ti and K13D-Ti were investigated. The increased failure strain of the FML was greater than that of carbon fibre-reinforced polymer (CFRP) matrix composites. The fatigue life of IMS60-Ti was much longer than that of K13D-Ti. The fatigue damage process in IMS60-Ti was related to the fatigue creep behaviour of the Ti-alloy face sheet and mode II cracking at the CFRP/Ti-alloy interface, and the damage in K13D-Ti was related to the K13D CFRP laminate. K E Y W O R D Scarbon/epoxy, damage, fatigue, fibre metal laminate, titanium alloy

show abstract

“…The fatigue material parameters are provided inTable 5. In this table the Paris law parameters ðC; mÞ and the values for fracture energy ðG Ic ; G IIc Þ are taken from[24,25] respectively. The value of g is our assumption.…”

mentioning

confidence: 99%