Design of state feedback controller for an auto pilot: to control the stability of aircraft pitch

摘要

Aircraft motion in 3D plane is considered to be of three rotations. First one is roll, second one is pitch and the third one is yaw. Pitch of an aircraft cannot be neglected and it is one of the key features to control an aircraft. The pitch of an aircraft is in unstable state space variable, which leads to instability of an aircraft and a control scheme is required to stabilize the aircraft. In this paper, we propose a control strategy which can stabilize the aircraft system. Simulation results using MATLAB are presented to demonstrate the efficiency of proposed control scheme.