International Journal of Engineering and Technology

An intelligent control system for the rocket engine during electromechanical stage is designed and scrutinized in this paper. The rocket is the only vehicle that lift-offs the spacecraft in the space. 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. So the orientation of the spacecraft in precise position is so critical. 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 linear quadratic regulator theory and setpoint weighted proportional integral derivative controller based on the two degree of freedom mathematical model. The transient behaviour of the LQR controller is not smooth and takes more time to settle in the defined position. Specific to the deficiencies of LQR, a setpoint weighted PID controller is proposed to improve the setpoint response. In conclusion, this paper compares the performance analysis of linear quadratic regulator and setpoint weighted PID controller. The simulation results indicate that the setpoint weighted PID controller has a remarkable improvement in terms of overshoot and settling time besides reducing steady state error. The proposed setpoint weighted PID controller enhances the system performance and produces enormous stability to the rocket engine.