Abstract
The ductile and fatigue behaviour of Al 2024 – T351 alloy is investigated using a local approach to damage evolution adopting continuum damage mechanics (CDM). The investigation involves uniaxial tensile test, load-unload tensile test and low cycle fatigue test at different strain amplitude. Fractographic examination of the failed surface helped to understand the involved mechanisms of fracture. Results indicate the material has good ductility and convincing fatigue life. This aluminum alloy is widely used in aircraft structure due to their high fatigue performance, easy formability, lower structural weight, higher damage tolerance and durability, much-needed quality parameters for weight specific aerospace applications. Damage mechanics based evaluations of this material are very scanty in published literature. The test results using damage parameters from experiments were tested in ABAQUS and flow behaviour is successfully reproduced to compare experimental results. Fatigue test results are compared well with Lemaitre model. The fractographic analysis clearly revealed the signature of ductile damage controlled fracture. The experiment on fatigue fractured specimen provided crack initiation, crack propagation and the final fracture zone clearly.
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