Enhancing the stabilization of the F-16 fighter aircraft pitch motion control via intelligent and classical method

Abstract

This thesis presents within the framework of a conceptual context simulation of our F-16 fighter aircraft model using the MATLAB/Simulink environment. A theoretical study on theaircraft F-16 will be presented in which a mathematical model was obtained using NewtonEuler formulism. The non-linear model was linearized and decoupled for both longitudinaland lateral directions around equilibrium points at certain trim conditions to obtain statespace models. This work aims at a complete study, analysis, design and performancemonitoring of the classical (LQR, PID, FLC) and the new robust generation controllers (Selftuning Fuzzy PID, GA-PID, 𝐻2/𝐻∞) in terms of flight trajectory reference tracking andstability augmentation of the pitch motion. From the results achieved a comparative analysiswill be investigated.