Application of intelligent controller in feedback control loop for aircraft pitch control

Abstract

This paper presents the investigation into the development of hybrid control scheme for pitch control of aircraft system. Proportional-integral-derivative (PID) and PID-type fuzzy logic controller are used in this investigation to control the pitch angle of aircraft system. The dynamic modeling of system begins with a derivation of suitable mathematical model to describe the longitudinal motion of an aircraft. The main motivation behind this research is to investigate which approach provides the best performance base on time response specification and disturbances rejection for an autopilot of longitudinal dynamic in pitch aircraft. Through the simulation in Matlab and Simulink results shows that, the PID-type fuzzy logic controller perform the best performance compared to classical controller technique, Proportional-Integral-Derivative (PID).