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Proceedings Paper

Modeling an adaptive impedance boundary condition device for helicopter individual blade control
Author(s): Fred Nitzsche
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Paper 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.

Paper Details

Date Published: 13 June 1997
PDF: 11 pages
Proc. SPIE 3039, Smart Structures and Materials 1997: Mathematics and Control in Smart Structures, (13 June 1997); doi: 10.1117/12.276540
Show Author Affiliations
Fred Nitzsche, National Research Council of Canada (Canada)

Published in SPIE Proceedings Vol. 3039:
Smart Structures and Materials 1997: Mathematics and Control in Smart Structures
Vasundara V. Varadan; Jagdish Chandra, Editor(s)

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