Modeling an adaptive impedance boundary condition device for helicopter individual blade control

Fred Nitzsche

doi:10.1117/12.276540

13 June 1997 Modeling an adaptive impedance boundary condition device for helicopter individual blade control

Fred Nitzsche

Proceedings Volume 3039, Smart Structures and Materials 1997: Mathematics and Control in Smart Structures; (1997) https://doi.org/10.1117/12.276540
Event: Smart Structures and Materials '97, 1997, San Diego, CA, United States

Abstract

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.

Citation Download Citation

Fred Nitzsche "Modeling an adaptive impedance boundary condition device for helicopter individual blade control", Proc. SPIE 3039, Smart Structures and Materials 1997: Mathematics and Control in Smart Structures, (13 June 1997); https://doi.org/10.1117/12.276540

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