Aeroelastic problems of tested rotor configurations can be processed using accurate knowledge and modelling of the structural dynamic behaviour and of the unsteady aerodynamic forces. For the individual disciplines, the physical anomalies of the rotating system need to be considered.
A comparison of the occurring stability phenomena on rotor craft with those on aircraft shows that by coupling the rotor and the elastic helicopter airframe there is already a possibility of instability of the mechanical system in the case of ground resonance. Moreover, in rotor blade flutter, classical bend-torsion coupling, such as that seen in rotors with blade joints, is present as well as other coupling mechanisms, such as those in joint-less rotors, which originate from the rotating parts.
The activities are described below: