An Adaptive Tuning Strategy of PID Attitude Control System

Abstract

This paper describes a procedure for tuning PID attitude control system of a launch vehicle. The key idea is a method based on a model reference adaptive system to estimate PID control gains. The launch vehicle is considered a rigid body. Since the performance specification is considered as a second order system and the close loop of the launch vehicle PID attitude control system has fourth order with two zeros, there is no matching between model reference and launch vehicle control system. The simulation results of the proposed tuning method are compared with a LQR method.