Abstract: APSTAR 6E satellite is the first full electric propulsion satellite in China. It is launched by a low cost rocket, and the separation orbit is LEO. In response to the characteristics of small thruster and long orbit transition, in order to shorten the orbit transition, the satellite to use the Separate Propulsion System for orbit raising, after completing the task, it can be thrown away. Due to the short working time in orbit, the Separate Propulsion System adopts a low cost design. This scheme presents a scheme of using Separate Propulsion System for orbit control and an autonomous departure after separation from satellite. This scheme reduces the dead weight brought by the Separate Propulsion System, reduces the time of orbit raising by electric propulsion, and reduces the consumption of xenon propellant, it has great advantages in improving the capacity and the service life of satellite.

Key words: full electric, propulsion separate propulsion system, orbit control