In the present investigation, the helicopter blade is modeled as a rotating beam with two degrees of freedom, namely the elastic flatwise bending and torsion. A mathematical model in the frequency domain is developed, incorporating the unsteady aerodynamic loads associated with helicopters in forward flight. The effects of dynamic adaptation of the rot boundary conditions on the beam aeroelastic response are studied. The results suggest that it is possible to control the local dynamic response at particular sections of the beam by varying the frequency and relative phase of the control signal.

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Conference Smart Structures and Materials 1997: Mathematics and Control in Smart Structures
Nitzsche, F. (1997). Modeling an adaptive impedance boundary condition device for helicopter individual blade control. In Proceedings of SPIE - The International Society for Optical Engineering (pp. 216–226).