Numerical simulation of the slant fracture of a helicopter's rotor hub with ductile damage failure criteria

• Published in: Fatigue & fracture of engineering materials & structures Vol. 35; no. 4; pp. 317 - 327
• Main Authors: GIGLIO, M., MANES, A., VIGANÒ, F.
• Format: Journal Article
• Language: English
• Published: Oxford, UK Blackwell Publishing Ltd 01.04.2012; Blackwell; Wiley Subscription Services, Inc
• Subjects: Alloys; Applied sciences; Computer simulation; Crack propagation; Criteria; ductile damage; Ductile fracture; Exact sciences and technology; experimental; Fatigue; fatigue crack; Fatigue failure; Fracture mechanics; Fractures; Mathematical models; Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology; Metals. Metallurgy; Numerical analysis; numerical model; Simulation; slant fracture; Ti-6Al-4V; Titanium base alloys; Helicopter; Rupture; Mechanical properties; Helicopter rotor; Ti―6Al―4V; Fatigue; experimental; Aluminium alloy; slant fracture; Aeronautic industry; ductile damage; Modeling; Titanium base alloys; Fatigue crack; numerical model; Numerical simulation; Application; Vanadium alloy
• ISSN: 8756-758X; 1460-2695
• DOI: 10.1111/j.1460-2695.2011.01622.x

ABSTRACT The 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.