In this thesis, a feasibility study on the attitude control function by using of several pulsed plasma thrusters(PPTs) is conducted. The PPT consumes less propellant mass for the velocity increase (ΔV) required for the orbit management or attitude control due to their high specific impulse characteristics, compared to traditional chemical or cold-gas propulsion systems. Thus the PPT is expected to be highly adequate for the missions such as long-duration operations and large ΔV orbit transfers. It also has relatively long operation time and is easy to implement. This thesis presents a study of the feasibility of the PPT for attitude control of spacecrafts in realistic missions. The classical PD controller and a fuzzy logic controller are tested to identify the feasibility of the PPT. And a fuel saving fuzzy controller is then proposed for more flexible mission performance.