An intelligent controller based fuzzy logic techniques for a morphing wing actuation system using shape memory alloy

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DOIResolve DOI: http://doi.org/10.2514/6.2011-2133
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TypeArticle
Proceedings titleCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Conference52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 4 April 2011 through 7 April 2011, Denver, CO
ISSN0273-4508
ISBN9781600869518
Article numberAIAA 2011-2133
SubjectActuation systems; Aerodynamic forces; Bench tests; Controller tuning; Defuzzifiers; Design phase; Experimental validations; Fuzzy logic techniques; Fuzzy models; Input-output mapping; Intelligent controllers; Laboratory conditions; Morphing wings; Position detection; Proportional integral derivatives; Real time; Transition point; Wind tunnel tests; Airfoils; Intelligent control; Structural dynamics; Wind stress; Fuzzy logic
AbstractThe paper presents a way to control the actuation lines of a morphing wing using an intelligent controller based on fuzzy logic techniques. The strong non-linear character of the used actuators, made from some smart materials, and the numerical simulations achieved in the design phase provides for the controller a fuzzy logic Proportional-Integral-Derivative architecture seconded by a conventional On-Off controller. The input-output mapping of the fuzzy model is designed, taking account of the system's error and its change in error. The shapes chosen for the inputs' membership functions are triangular, while the product fuzzy inference and the center average defuzzifier are applied (Sugeno). After the controller tuning, three validation steps are done: a numerical one, followed by other two experimentally. For the experimental validation, bench tests and wind tunnel tests are performed. The bench test experimental validation is made in laboratory conditions, in the absence of aerodynamic forces, for different actuation commands. In the wind tunnel tests, are also experimentally validated the optimized airfoils with the theoretically- determined airfoils obtained earlier. Both the transition point real time position detection and visualization are realized in wind tunnel tests. Copyright © 2011 by Ruxandra M Botez.
Publication date
LanguageEnglish
AffiliationNational Research Council Canada (NRC-CNRC)
Peer reviewedYes
NPARC number21271693
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Record identifierc608a074-31a8-4b73-bd1a-b29311155cd5
Record created2014-03-24
Record modified2016-05-09
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