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

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

dc.contributor.author	Hill, WJ	en
dc.contributor.author	Strganac, TW	en
dc.contributor.author	Nichkawde, C	en
dc.contributor.author	McFarland, DM	en
dc.contributor.author	Kerschen, G	en
dc.contributor.author	Lee, YS	en
dc.contributor.author	Vakakis, AF	en
dc.contributor.author	Bergman, LA	en
dc.date.accessioned	2014-03-01T02:50:54Z
dc.date.available	2014-03-01T02:50:54Z
dc.date.issued	2006	en
dc.identifier.issn	02734508	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/35192
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-34147129182&partnerID=40&md5=98492b5448ed7554a9e0f967d52e5f0c	en
dc.subject.other	Energy pumping	en
dc.subject.other	Energy sinks	en
dc.subject.other	Limit cycle oscillations	en
dc.subject.other	Aircraft	en
dc.subject.other	Degrees of freedom (mechanics)	en
dc.subject.other	Flight control systems	en
dc.subject.other	Space flight	en
dc.subject.other	Aerodynamics	en
dc.title	Suppression of aeroelastic instability with a nonlinear energy sink: Experimental results	en
heal.type	conferenceItem	en
heal.publicationDate	2006	en
heal.abstract	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.	en
heal.journalName	Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference	en
dc.identifier.volume	5	en
dc.identifier.spage	3145	en
dc.identifier.epage	3157	en