On the necessity of high-fidelity aeroelastic modeling of on-blade control surface for helicopter vibration suppression

Ulker, FD; Voutsinas, S; Riziotis, V; Nitzsche, F

dc.contributor.author	Ulker, FD	en
dc.contributor.author	Voutsinas, S	en
dc.contributor.author	Riziotis, V	en
dc.contributor.author	Nitzsche, F	en
dc.date.accessioned	2014-03-01T02:53:58Z
dc.date.available	2014-03-01T02:53:58Z
dc.date.issued	2012	en
dc.identifier.issn	15522938	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/36509
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-84864924331&partnerID=40&md5=e7524709e6b59cc9830813339e97de27	en
dc.subject.other	Aero-elastic simulations	en
dc.subject.other	Aerodynamic loading	en
dc.subject.other	Aeroelastic modeling	en
dc.subject.other	Aeroelastic response	en
dc.subject.other	Blade-wake interactions	en
dc.subject.other	Closed-loop instability	en
dc.subject.other	Control surface deflection	en
dc.subject.other	Controller synthesis	en
dc.subject.other	Critical effects	en
dc.subject.other	Critical frequencies	en
dc.subject.other	Forward flight	en
dc.subject.other	Frequency contents	en
dc.subject.other	Helicopter vibration	en
dc.subject.other	High-fidelity simulations	en
dc.subject.other	Lifting Line Theory	en
dc.subject.other	Reduced order models	en
dc.subject.other	Rotating frame	en
dc.subject.other	Rotor blades	en
dc.subject.other	Rotor systems	en
dc.subject.other	Aeroelasticity	en
dc.subject.other	Controllers	en
dc.subject.other	Helicopters	en
dc.subject.other	Vortex flow	en
dc.subject.other	Wakes	en
dc.subject.other	Control surfaces	en
dc.title	On the necessity of high-fidelity aeroelastic modeling of on-blade control surface for helicopter vibration suppression	en
heal.type	conferenceItem	en
heal.publicationDate	2012	en
heal.abstract	This paper presents critical effects of on-blade active control surface motion on the aeroelastic response of a rotor blade in forward flight. Aeroelastic simulations conducted with an in-house high fidelity solver indicate that blades-wake interactions caused by control surface deflections change the frequency content of the rotating frame blade loads. Specifically at the 11 rev frequency for a four-bladed rotor system this effect is predominant. The previously recorded information on variations in aerodynamic loading obtained from lifting line theory and comprehensive grid and/or vortex based solvers are shown to be due to blade-wake modeling differences. To prevent possible closed-loop instabilities at the control critical frequencies, either in controller synthesis these modeling differences must be accounted for or the reduced-order models used in controller synthesis must be identified from high-fidelity simulations to accurately capture these blade-wake interactions. Copyright © 2012 by the American Helicopter Society International, Inc. All rights reserved.	en
heal.journalName	Annual Forum Proceedings - AHS International	en
dc.identifier.volume	2	en
dc.identifier.spage	1270	en
dc.identifier.epage	1279	en