A simulated intelligent controller for aircraft pitch control
Siti Marhainis, Othman
Nasrul Helmei, Halim
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This paper is present about a simulated intelligent controller for aircraft pitch control. This project uses two types of controllers such as PID controller and fuzzy logic controller. Both types of controllers will be compared to the best results can be obtained. The purpose is to use the controller for controlling the aircraft pitch angle. Results shown in MATLAB Simulink. This project is a closed loop system. Where there are step, controller, plant, output and feedback. PID controller have three term controller such as Proportional gain (Kp), Integral gain (Ki) and Derivative gain (Kd). Fuzzy logic controller (FLC) is a second controller in this project. This controller developed for control the pitch of an aircraft system. Simulation results with respect to the response of the pitch angle and pitch rate are presented based on common’s criteria of step response. Finally, the performances of pitch control systems are examined and analyzed in terms of percent of overshoot, rise time, settling time and steady state error in order to identify how good the response of the controller. GUI will be developed by using MATLAB to view the response of the simulated of pitch control system.
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