Abstract: According to the need of control accuracy for eastwest station keeping of geostationary satellites, an optimization method of orbitcontrol parameters and propellant consumption are proposed. Considering the satellite orbital dragging force induced by attitudecontrol injection, the ignition time of orbitcontrol thrusters is compensated. The propellant consumption is estimated according to the ignition time of all thrusters. Some examples of the optimization process are given as illustration to show that the method is effective and correct, which can be used to correct the orbitcontrol strategy in practice.