The more electric aircraft initiative represents a major technological leap forward for the aircraft industry. The traditional hydraulic systems are progressively being replaced by electromechanical actuators (EMAs). This research presents the modelling and controller (PID, Conventional Smith predictor and Advanced Smith predictor) design of electromechanical flap actuation system in a more electric aircraft. In addition to PID controller, conventional Smith predictor and advanced Smith predictor are implemented to compensate the time delay present in practical system. The main requirement for the controller is overshoot is minimum flap deflection (\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\le 0.3 $$\end{document}). Because a small change in flap angle affects the wing camber and the angle of attack (AOA). Since the conventional and advanced Smith predictor contain predictor part, they compensate the delay presented in practical system. In addition to predictor part, the advanced Smith predictor contains three controllers. This will help to improve the overall performance of the system by disturbance rejection and servo tracking.


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    Title :

    Controller for Electromechanical Flap Actuation System in More Electric Aircraft


    Additional title:

    Lect. Notes in Networks, Syst.




    Publication date :

    2023-02-17


    Size :

    15 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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