Abstract
ABSTRACTThe main rotor hub is one of the most critical components in helicopter structures. Thus, to assess the behaviour of the component, a fatigue test until failure has been carried out on a real Ti–6Al–4V hub. A fracture mechanics analysis is used to estimate the critical crack dimensions. Subsequently, the slant fracture due to a propagating fatigue crack has also been simulated numerically with an explicit finite element model, using the Bao–Wierzbicki ductile damage criterion. Fracture toughness and failure calibration of Ti alloy have been carried out to obtain reliable results. The numerical fracture surface obtained has been compared with the experimental one.
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