Fatigue crack growth and delamination behaviours of advanced Al‐Li alloy laminate under single tensile overload
Source abstract
Abstract
Abstract In this paper, fatigue crack growth and delamination behaviours of a new fibre metal laminate (FML) named as Al‐Li alloy laminate were tested under different single tensile overloads and compared with those of glass laminate aluminium reinforced epoxy. The results indicate that the crack growth rate of Al‐Li alloy laminate after overload applied can quickly get back to its original level when the crack grows outside of the overload plastic zone. The overload has no influence on the delamination shape and size of Al‐Li alloy laminate. These results are obviously different from those found in the present study for GLARE, in which the crack growth rate cannot recover after overload, even though the crack is far beyond the overload plastic zone. A kink nearby the location of overload applied was found in the obtained delamination shape. This study provides some new results for better understanding the damage tolerance mechanism of FMLs.
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Research context
OpenAlex topics: Mechanical Behavior of Composites · Fatigue and fracture mechanics · Structural Behavior of Reinforced Concrete
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Beijing Institute of Aeronautical Materials Beijing 100095 China
Beijing Aeronautical Science & Technology Research Institute of COMAC Beijing 102211 China
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