Aircraft Pitch Control System Using LQR and Fuzzy Logic Controller

Abstract

This paper presents a comparative assessment of modern and intelligent controllers based on time response
specification performance for a pitch control of an aircraft system. The dynamic modeling of pitch control system is
performed and an autopilot that controls the pitch angle of an aircraft is designed using two controller design methods.The
transfer function for pitch control surface is derived and two separate controllers, Proportional integral Derivative and
Fuzzy Logic Controller (FLC) are designed for controlling the pitch angle. The effectiveness of each controller is tested and
verified using Matlab/Simulink platform. It is found from simulation, fuzzy logic controller give the best performance
compared to PID controller.