The application of error quaternion and PID control method in Earth observation satellite´s attitude control system

Because of its payload´s work characteristic, it requires much higher precision in Earth observation satellite´s attitude control systems than others. Most Earth observation satellites use zero-momentum three-axis stabilization control method. This paper investigates this control method in satellite control system, deducing the dynamics and kinematics of satellite attitude´s model expressed by attitude error quaternion, applying PID control method in this model, and then simulating and evaluating the method preliminarily. The results show that the method can achieve the require precision quickly