Optimal transfer orbit trajectory using electric propulsion

摘要

An apparatus and method for translating a spacecraft (10) from an injection orbit (16) about a central body (12) to geosynchronous orbit (18) in a time efficient manner. The spacecraft (10) includes propulsion thrusters (50) which are fired in predetermined timing sequences controlled by a controller (64) in relation to the apogee (66) and perigee (72) of the injection orbit (16) and successive transfer orbits (74, 76).