Dynamics of rotating piezoelectric fiber composite beams

The concept of an active beam can be applied to helicopter rotor blades in order to reduce vibrations and noise due to different aeroelastic interactions. The most effective way to actively influence the blade dynamics is to make use of the aerodynamic forces by changing the angle of attack. Thus the goal is to investigate the potential of induced torsion and its different possible actuation schemes on the dynamic behavior of the rotating system. Starting with the description of the rotor kinematics and having regard to the active beam constitutive relations the principle of virtual work is established. In order to obtain a solution, the arising system of equations is discretized using the finite element approach and thus the equations of motion are derived. The eigenvalue problem is solved and results are compared to an analysis with finite shell elements conducted with a commercial code. Finally the complete solution, providing the response of the rotating system to a harmonic piezoelectrically induced excitation, is obtained.