The application of electric propulsion engines to attitude control and stationkeeping of 24-hour stationary satellites is analyzed and compared with the performance of contemporary cold gas, monopropellant, and bipropellant propulsion systems. Both a 500-pound spin-stabilized and a 1500-pound three-axis controlled satellite compatible with current boost vehicles are examined, and each type of propulsion system compared as a function of mission duration and maneuver requirements. Solar electric propulsion is shown to be superior to chemical propulsion for long term stationkeeping and three-axis attitude control of the larger satellite. Cold gas and chemical propulsion are superior for attitude control and provide strong competition for electric propulsion in the stationkeeping of the smaller spin-stabilized satellite. (auth)