Terminal ballistic effect on the crack growth assessment of a helicopter rotor drive

An experimental impact test of a 7.62 NATO projectile perforating a helicopter tail rotor shaft is briefly presented. With the aim to reproduce the operational worst case, the damage occurs during the flight, the impacted specimen is subsequently tested with a multiaxial testing machine. This procedure allows the evaluation of the capability of the shaft to withstand a recovery mission, which is simulated by applying a torsional fatigue spectrum to the shaft. The nucleation and propagation of fatigue cracks have been monitored during the test. element analyses have been carried out to simulate both impact and crack propagation. The state of stress is multiaxial: it is induced by torque, residual stress field and shape of the damage. Mixed mode propagation has hence been considered by means of an equivalent SIF. Numerical results are in agreement with experimental data.