A hybrid fuzzy logic proportional-integral-derivative and conventional on-off controller for morphing wing actuation using shape memory alloy: part 2, controller implementation and validation

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TypeArticle
Journal titleThe Aeronautical Journal
ISSN0001-9240
Volume116
Issue1179
Pages451465; # of pages: 15
SubjectAerodynamic forces; Controller implementation; Data acquisition cards; Experimental bench; Experimental validations; Hybrid actuation; Hybrid controller; Laboratory conditions; Linear variable differential transformer; Matlab/Simulink software; Morphing wings; Output channels; Physical model; Position detection; Power supply; Proportional integral derivatives; Simulation and validation; SMA wire; Switching power supplies; Transition point; Wind tunnel tests; Actuators; Aerodynamics; Data acquisition; Electric power supplies to apparatus; Fuzzy logic; Power electronics; Shape memory effect; Thermocouples; Visualization; Voltage dividers; Proportional control systems
AbstractThe paper presents the numerical and experimental validation of a hybrid actuation control concept - fuzzy logic proportional-integral-derivative (PID) plus conventional on-off - for a new morphing wing mechanism, using smart materials made of shape memory alloy (SMA) as actuators. After a presentation of the hybrid controller architecture that was adopted in the Part 1, this paper focuses on its implementation, simulation and validation. The PID on-off controller was numerically and experimentally implemented using the Matlab/Simulink software. Following preliminary numerical simulations which were conducted to tune the controller, an experimental validation was performed. To implement the controller on the physical model, two programmable switching power supplies (AMREL SPS100-33) and a Quanser Q8 data acquisition card were used. The data acquisition inputs were two signals from linear variable differential transformer potentiometers, indicating the positions of the actuators, and six signals from thermocouples installed on the SMA wires. The acquisition board's output channels were used to control power supplies in order to obtain the desired skin deflections. The experimental validation utilised an experimental bench test in laboratory conditions in the absence of aerodynamic forces, and a wind-tunnel test for different actuation commands. Simultaneously, the optimised aerofoils were experimentally validated with the theoreticallydetermined aerofoils obtained earlier. Both the transition point real time position detection and visualisation were realised in wind tunnel tests.
Publication date
PublisherRoyal Aeronautical Society
LanguageEnglish
AffiliationNational Research Council Canada; Aerospace
Peer reviewedYes
NPARC number21270020
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Record identifier2061a465-d574-4711-8097-66b12cd76159
Record created2013-12-13
Record modified2017-01-13
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