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Kammegne M.J.T.,Laboratory of Applied Research in Active Controls | Belhadj H.,Laboratory of Applied Research in Active Controls | Nguyen D.-H.,Laboratory of Applied Research in Active Controls | Botez R.M.,Laboratory of Applied Research in Active Controls
Proceedings of the IASTED International Conference on Modelling, Identification and Control | Year: 2015

This paper describes the design of a double loop fuzzy logic position and torque controller for wing morphing using brushed DC motors as actuators. The DC motor is used in this application as an actuator to change the shape of a wing upper surface. To morph the wing with these actuators, a mechanical system coupled to the actuators is integrated in the wing. The fuzzy logic technique is used to design two controllers: one for the position and the other for the torque, to control the position and the torque of the each actuator. The controllers are validated numerically with Matlab/Simulink software, followed by a physical implementation of the control and experimental validation setup in the PRICE-PAÏDOUSSIS wind tunnel. The physical implementation is realized using a programmable power supply, the CPX400. The actuators are connected to the output of the power supply and the output of the torque controller, which is the command signal (voltage), is sent to the input of the programmable power supply. In addition to the design of the fuzzy controllers (position and current controller), their performance is compared to that of a Proportional Integral Derivative controller designed and experimentally tested in a previous approach. © 2015, Acta Press. All rights reserved.


Murrieta-Mendoza A.,Laboratory of Applied Research in Active Controls | Botez R.M.,Laboratory of Applied Research in Active Controls | Ford S.,Esterline
Proceedings of the IASTED International Conference on Modelling, Identification and Control | Year: 2014

This paper proposes a new method for estimate the fuel burned and the emissions generated such as CO2 and NOx during a missed approach procedure. This method use information from the air pollutant emissions inventory guidebook created by the Emission Inventory Guidebook from the European Environment agency to perform the computations. The descend phase was separated in two different mode, one composed by climb, cruise and descent, and the other by the landing to takeoff mode. The calculations are made with the help of an interpolation polynomial for the mode in function of distance and with the flight time for the mode in function of time. Missed approach calculations can be used as a decision tool to select between the costs of different routes and determine the most convenient in devices such as the Flight Management System or by ground automated systems assisting flight controllers.


Rodriguez L.F.,University of Quebec at Montréal | Rodriguez L.F.,Laboratory of Applied Research in Active Controls | Botez R.M.,University of Quebec at Montréal | Botez R.M.,Laboratory of Applied Research in Active Controls
Journal of Propulsion and Power | Year: 2013

A generic model was proposed that can predict engine thrust for turbofan engines in the whole flight envelope. The model was validated with available experimental data for four engines, Honeywell's TFE 731-5, General Electric's TF39, Garrett's ATF3, and General Electric's CF6-80. In the proposed model, the static sea level thrust is taken as a reference that will be multiplied by a thrust coefficient, thereby obtaining the actual thrust at each flight condition. The thrust coefficient is divided into two subcoefficients, the first subcoefficient models altitude effects, and the second subcoefficient models the Mach effects. The effects of Mach number, modeled using the coefficient, are divided into three submodels because the physical phenomena involved in the air caption by the engine change at the different altitudes under evaluation. It was found that the model has a very good accuracy at all Mach numbers and their corresponding altitudes.


Kammegne M.J.T.,Laboratory of Applied Research in Active Controls | Grigorie T.L.,Laboratory of Applied Research in Active Controls | Botez R.M.,Laboratory of Applied Research in Active Controls | Koreanschi A.,Laboratory of Applied Research in Active Controls
Proceedings of the IASTED International Conference on Modelling, Identification and Control | Year: 2014

Conventional or brushed DC motors are often used for many industrial applications. A large variety of these motors is found in automation, medical, robotics and aeronautical fields. In this paper, the design and experimental validation of a position controller for a morphing wing design application is presented. Matlab/Simulink was used to design the Proportional Integral Derivative controller. For experimental validation, tests were carried out in the Price-Païdoussis subsonic blow down wind tunnel. The upper wing surface was deformed by means of a mechanical system consisting of two eccentric shafts. Both are connected to electrical actuators. Comparisons of two sets of results are provided in this paper. The first set is related to control validation and the second set is related to aerodynamic validation.

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