A method of eccentricity control for a geosynchronous satellite having a geosynchronous orbit with an orbit line of nodes, the method comprising: setting a schedule for the eccentricity control of the geosynchronous orbit using a two-dimensional eccentricity vector ellipse describing target eccentricity vector components over an annual period, each of the eccentricity vector components indicating a magnitude and direction for eccentricity vectors of the geosynchronous orbit; defining a plurality of parameters for the two-dimensional eccentricity vector ellipse including a centroid for a control locus, the control locus defining the target eccentricity vector components for the eccentricity vector ellipse in two-dimensional space, and a semi-major axis and a semi-minor axis of the control locus determining an elliptical shape of the two-dimensional eccentricity vector ellipse, the semi-major axis of the control locus aligning with the orbit line of nodes and having a maximal length equal to a maximum natural uncontrolled eccentricity of the geosynchronous orbit, the semi-minor axis having a nonzero length less than a length of the semi-major axis; and transmitting operational commands to the geosynchronous satellite for eccentricity control based on the schedule and the two-dimensional eccentricity vector ellipse, the operational commands defining maneuvers and inter-maneuver uncontrolled eccentricity coast segments to maintain a geodetic longitude of the geosynchronous satellite within a predefined distance from a station longitude. setting a schedule for the eccentricity control of the geosynchronous orbit using a two-dimensional eccentricity vector ellipse describing target eccentricity vector components over an annual period, each of the eccentricity vector components indicating a magnitude and direction for eccentricity vectors of the geosynchronous orbit; defining a plurality of parameters for the two-dimensional eccentricity vector ellipse including a centroid for a control locus, the control locus defining the target eccentricity vector components for the eccentricity vector ellipse in two-dimensional space, and a semi-major axis and a semi-minor axis of the control locus determining an elliptical shape of the two-dimensional eccentricity vector ellipse, the semi-major axis of the control locus aligning with the orbit line of nodes and having a maximal length equal to a maximum natural uncontrolled eccentricity of the geosynchronous orbit, the semi-minor axis having a nonzero length less than a length of the semi-major axis; and a centroid for a control locus, the control locus defining the target eccentricity vector components for the eccentricity vector ellipse in two-dimensional space, and a semi-major axis and a semi-minor axis of the control locus determining an elliptical shape of the two-dimensional eccentricity vector ellipse, the semi-major axis of the control locus aligning with the orbit line of nodes and having a maximal length equal to a maximum natural uncontrolled eccentricity of the geosynchronous orbit, the semi-minor axis having a nonzero length less than a length of the semi-major axis; and transmitting operational commands to the geosynchronous satellite for eccentricity control based on the schedule and the two-dimensional eccentricity vector ellipse, the operational commands defining maneuvers and inter-maneuver uncontrolled eccentricity coast segments to maintain a geodetic longitude of the geosynchronous satellite within a predefined distance from a station longitude.