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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

Published online by Cambridge University Press:  27 January 2016

T. L. Grigorie ,
R. M. Botez ,
A. V. Popov ,
M. Mamou  and
Y. Mébarki
T. L. Grigorie
Affiliation:
École de Technologie Supérieure, Montréal, Québec, Canada
R. M. Botez
Affiliation:
École de Technologie Supérieure, Montréal, Québec, Canada
A. V. Popov
Affiliation:
École de Technologie Supérieure, Montréal, Québec, Canada
M. Mamou
Affiliation:
National Research Council, Ottawa, Ontario, Canada
Y. Mébarki
Affiliation:
National Research Council, Ottawa, Ontario, Canada
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Abstract

The 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 theoretically-determined aerofoils obtained earlier. Both the transition point real time position detection and visualisation were realised in wind tunnel tests.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1179 , May 2012 , pp. 451 - 465
Copyright
Copyright © Royal Aeronautical Society 2012 

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