Optimal transfer orbit trajectory using electric propulsion

The present invention relates to a spacecraft (10) injection orbit (16) from around a central body (12) is transferred by way of a time factor to a geosynchronous orbit (18) of the apparatus and methods, the spacecraft (10) includes propulsion thrusters (50), which can be a controller (64) controls, ignite within a predetermined time sequence, and with the injection orbit (16) and the subsequent transfer orbit (74, 76) of the apogee (66) and perigee (72 )related.