AUTOMATIC CONTROL SYSTEM OF THE AIRCRAFT YAW'S ANGLE USING A PROPORTIONAL - INTEGRATOR - DERIVATIVE CONTROL LAW

摘要

This paper presents a study of a system for the automatic control of the yaw's angle, with angular velocity feedback E.E. (execution element) and proportional -integrator - derivative (P.I.D.) control law. Starting from the block diagram of the system, one studies the stability and the performances of the system. For this purpose an algorithm has been successfully implementated in Matlab/Simulink. For three aircraft types, one obtained the transfer functions, poles, zeros, dimensional and non-dimensional transmission ratios, time variations of the yaw's angle, time variations of the direction deflection and so on.