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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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