Research on Attitude System of Active Magnetic Control Small Satellite

When enter orbit, small satellite often tumble as a result of disturbance. How to capture it promptly with finite magnetic torque is an important problem. Because of the coupling of dynamics and control, the small satellite control system is a nonlinear attitude control system with bounds. For high direction and steady precision, an effective method must be found. In this paper, combining with the bound conditions of magnetic torque, two methods are researched. The first is energy method. It use Lyapunov energy depletion theory, taking the Lyapunov function as a target function, determine the magnetic torque. Secondly the decoupling variable structure control theory is used to deal the magnetic torque. The results of computer simulation indicate that these methods have advantages of excellent robustness and easily designed and realized.