Optimizing the Dynamic Response of Microsatellite Yaw-axis Attitude Using LQR-Based Control System

Abstract

The importance of effective satellite attitude control system is that it can ensure both quality and reliability of data acquisition by a microsatellite. In this paper, an optimal controller is designed for microsatellite yaw-axis attitude control system. In order to achieve this, the dynamic models of microsatellite yaw-axis attitude are obtained. Then an optimal controller based on Linear Quadratic Regulator (LQR) is designed. The designed LQR is integrated into the closed loop network of the microsatellite yaw-axis attitude control system. A MATLAB/Simulink model, which is computer-based model, is developed using the mathematical models of the closed control system. The MATLAB/Simulink model was used to conduct computer simulation of microsatellite attitude with the LQR. The simulation analysis revealed that the proposed LQR improve the transient and steady-state performance of the system in terms of rise time, settling time, overshoot, and steady-state error.