Suppression of aeroelastic instability with a nonlinear energy sink: Experimental results

The presence of limit cycle oscillations within the flight envelopes of existing aircraft is well documented. Future air vehicle designs are also likely to encounter limit cycle oscillations under certain loading conditions. These steady-state constant amplitude oscillations are detrimental to mission effectiveness and lead to increased fatigue of aircraft structures. Previous efforts to suppress limit cycle oscillations have focused primarily on active control methods. These efforts have been effective but require significant measurement and control resources. In this study the investigators test a passive method for suppressing limit cycle behavior. A nonlinear energy sink, based on the principle of nonlinear energy pumping, is shown to be effective for increasing the stability threshold of a nonlinear two degree of freedom aeroelastic system. Copyright © 2006 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

Hill, W. J., Strganac, T. W., Nichkawde, C., McFarland, D. M., Kerschen, G., Lee, Y. S., Vakakis, A. F., & Bergman, L. A.

Hill, WJ||Strganac, TW||Nichkawde, C||McFarland, DM||Kerschen, G||Lee, YS||Vakakis, AF||Bergman, LA

Suppression of aeroelastic instability with a nonlinear energy sink: Experimental results Conference Paper