The model for the liquidfilled spacecraft was established,where the viscous boundary layer model was developed to predict energy dissipation rates and liquid damping in fullyfilled tank of spacecraft. The equivalent gain for the torques feedback was carried out, and the control logic was decided to determine when the separatrix has been crossed and when thrusters must be fired. Spacecraft spinning about its minor axis in the presence of energy dissipation is directionally unstable. Correspondingly, the spacecraft can end up with either a positive or a negative major axis spin due to the energy lost in fuel sloshing and vibration, which cannot be determined a priori. The results presented demonstrate that the reorientation maneuver can be completed by pulse thrust, which provides a desired final orientation.