Novel controller design demonstration for vibration alleviation of helicopter rotor blades

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DOIResolve DOI: http://doi.org/10.1117/12.917520
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TypeArticle
Proceedings titleActive and Passive Smart Structures and Integrated Systems 2012
Proceedings of SPIE
ConferenceActive and Passive Smart Structures and Integrated Systems 2012, March 12-15, 2012, San Diego, CA, USA
ISSN0277-786X
ISBN9780819489982
Volume8341
Article number834108
SubjectAdvanced controller; Aero-elastic simulations; Aerodynamic loading; Closed loop stability; Computational costs; Controller designs; Controller synthesis; Helicopter vibration control; High fidelity; Linear matrix inequality formulations; Periodic Riccati equation; Synthesis problems; Trailing edges; Integrated control; Linear matrix inequalities; Riccati equations; Turbomachine blades
AbstractThis paper presents an advanced controller design methodology for vibration alleviation of helicopter rotor systems. Particularly, vibration alleviation in a forward ight regime where the rotor blades experience periodically varying aerodynamic loading was investigated. Controller synthesis was carried out under the time-periodic H 2 and H∞ framework and the synthesis problem was solved based on both periodic Riccati and Linear Matrix Inequality (LMI) formulations. The closed-loop stability was analyzed using Floquet-Lyapunov theory, and the controller's performance was validated by closed-loop high-fidelity aeroelastic simulations. To validate the controller's performance an actively controlled trailing edge ap strategy was implemented. Computational cost was compared for both formulations.
Publication date
LanguageEnglish
AffiliationAerospace; National Research Council Canada
Peer reviewedYes
NPARC number21270181
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Record identifierb6fb9cf4-9e5b-422f-9d57-3267b98921e7
Record created2014-01-08
Record modified2016-05-09
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