A method for controlling a plurality of satellites, the method comprising: establishing a first inclination vector associated with a first satellite of the plurality of satellites; establishing a second inclination vector associated with a second satellite of the plurality of satellites; controlling the first satellite and the second satellite, such that the first satellite and the second satellite are synchronized with a node; averaging a value of a right ascension of the node for at least one of the first inclination vector and the second inclination vector over a period of a control cycle; managing a plurality of predominately tangential corrections for at least one of the first satellite and the second satellite such that an eccentricity vector, directed at perigee, is substantially collinear with and substantially tracks the at least one of the first inclination vector and the second inclination vector such that latitude control of the at least one of the first satellite and the second satellite is not required to maintain the at least one of the first satellite and the second satellite in an orbit; minimizing a maximum variation of the eccentricity vector based on an orbit initialization; reducing the eccentricity vector to facilitate maintaining a longitude of at least one of the first satellite and the second satellite within a predetermined slot; averaging at least one of the first inclination vector and the second inclination vector over the period of the control cycle; and managing corrections for the at least one of the first satellite and the second satellite such that the eccentricity vector rotates at substantially the same rate as the at least one of the average first inclination vector and the average second inclination vector. establishing a first inclination vector associated with a first satellite of the plurality of satellites; establishing a second inclination vector associated with a second satellite of the plurality of satellites; controlling the first satellite and the second satellite, such that the first satellite and the second satellite are synchronized with a node; averaging a value of a right ascension of the node for at least one of the first inclination vector and the second inclination vector over a period of a control cycle; managing a plurality of predominately tangential corrections for at least one of the first satellite and the second satellite such that an eccentricity vector, directed at perigee, is substantially collinear with and substantially tracks the at least one of the first inclination vector and the second inclination vector such that latitude control of the at least one of the first satellite and the second satellite is not required to maintain the at least one of the first satellite and the second satellite in an orbit; minimizing a maximum variation of the eccentricity vector based on an orbit initialization; reducing the eccentricity vector to facilitate maintaining a longitude of at least one of the first satellite and the second satellite within a predetermined slot; averaging at least one of the first inclination vector and the second inclination vector over the period of the control cycle; and managing corrections for the at least one of the first satellite and the second satellite such that the eccentricity vector rotates at substantially the same rate as the at least one of the average first inclination vector and the average second inclination vector.