Abstract: A method, apparatus, article of manufacture, and a memory structure for controlling the eccentricity of an orbit. One embodiment of the present invention is described by a method comprising the step of performing a program of eccentricity control maneuvers wherein the control maneuvers are executed at times and in directions selected to apply substantially all eccentricity control along a line of antinodes. In one embodiment, the control maneuvers arc tangential maneuvers, and each control maneuver is applied near the line of antinodes. Provision is made for performing additional maneuvers, including node retargcting maneuvers during specified intervals. Another embodiment of the invention is described by a satellite in a substantially geosynchronous orbit having a satellite control system with a processor implementing instructions to perform control maneuvers as described above.