Failure analysis of a composite main rotor helicopter hub

A full scale fatigue test of a helicopter main rotor hub MR/H has been performed by spectrum loading. The test has been supported by a detailed finite element model of the component providing relevant information about its behaviour under loading. The MR/H has been made of Ti–6Al–4V wrapped up by a circular carbon band. Stress and strain from FE model have been validated by strain survey addressing the most critical locations. Fatigue life evaluation has been carried out by analysis in good agreement with the test results. The combined approach by test and validated numerical models has proved to be a reliable tool for fatigue substantiation of critical parts.