Pitch and yaw attitude control of a rocket engine using hybrid fuzzy-pid controller

Abstract

The rocket is the only vehicle that launches the spacecraft in the space. The orientation of the spacecraft in precise position is so crucial. But, the motion of the rocket can be influenced by internal and external disturbances. Furthermore, the rocket is a multi-input and multi-output nonlinear system whose dynamics are unstable and poorly understood. Hence, attitude control of the rocket is a big challenge with real time. To make the rocket stable against the influences, this paper has examined the control technology such as proportional integral derivative control using anti-windup mechanism and linear quadratic regulator theory based on the degree of freedom mathematical model. The transient behaviour of both the controller is not smooth and takes more time to settle in the defined location. Specific to the deficiencies of PID and LQR, the proportional integral derivative controller is combined with a fuzzy logic controller to overcome the defects of PID and LQR. In conclusion, this paper compares the performance analysis of fuzzy-PID controller with linear quadratic regulator and proportional integral derivative controller. The simulation results indicate that the hybrid fuzzy-PID controller has a remarkable improvement in terms of overshoot and settling time besides reducing steady state error. The proposed hybrid fuzzy-PID controller eliminates the overshoot completely and produces enormous stability to the rocket engine.