Pitch Controller For Aeroplane Using PID Method

Ahmad Syazwan, Che Muhamad (2009) Pitch Controller For Aeroplane Using PID Method. Project Report. UTeM, Melaka, Malaysia. (Submitted)

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Abstract

The purpose of this project is about to design a Pitch controller for aeroplane control using PID control algorithms. In this project, pitch controller are generally controlled by Proportional-Integral-Derivative (PID) controllers. The PlD controller method was implemented into the pitch controller in this project. A PID controller is a generic control loop feedback mechanism widely used in control systems. The PID controller calculation involves three separate parameters; the proportional, the integral and derivatives values. The proportional value determines the reaction to the current error, the integral determines the reaction based on the sum of recent errors and derivative determines the reaction to the rate at which the error has been changing. The weighted sum of these three actions is outputted to a control the pitch rate of plane. By tuning the three constants in the PID controller algorithm the PID can provide control action designed for specific process requirements. The response of the controller can be described in terms of the responsiveness of the controller to an error, the degree to which the controller overshoots the set point and the degree of system oscillation. Finally, the conclusion and suggestion to improve this project is state for the future study.

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