Processing aeroelastic problems requires an accurate knowledge and modelling of the structural dynamic behaviour of the examined configuration. For rotor craft this requires a precise physical description of the rotor with the additional description of the stiffness and damping generated by the rotation effect as well as its coupling with the non-rotating fuselage.
This leads to increasing demands on the experimental (component tests, overall tests) and on the simulation studies (Finite Element Method (FEM) for substructures, multiple component dynamics for the overall system), which are carried out in internal projects or with industry partners.
The activities are described below: