In this paper, the complex nonlinear dynamics of a satellite which is modelled after KITSAT is obtained. And it is shown that several limitations exist when the magnetorquer is used as an active actuator to attitude control. Such limitations cause a delayed convergence of pitch and roll angle. The simulation results insure that the roll angle bias is dependent on the z axis spin rate. And two methods(feedback and fuzzy control) are applied to control the attitude libration through the computer simulations. The computer simulation results for two methods are presented.
