Eccentricity control strategy for inclined geosynchronous orbits

A method of performing maneuvers to reduce a drift of an orbit while simultaneously controlling an eccentricity of the orbit, comprising the step of:

• performing a program of control maneuvers to control drift at tunes and in directions to apply substantially all eccentricity control (Δeman) along the line of antinodes such that an argument of perigee of the satellite orbit during the at least one year changes by greater than 180 degrees if the program of control maneuvers are performed for at least one year.

A satellite in a substantially geosynchronous orbit characterizable by a line of antinodes, comprising:

• a satellite control system having a processor and a plurality of thrusters, wherein the processor implements instructions commanding the thrusters to perform a program of control maneuvers at times and in directions to apply substantially all eccentricity control (Δeman) along the line of antinodes such that an argument of perigee of the satellite orbit during the at least one year changes by greater than 180 degrees if the program of control maneuvers are performed for at least one year.

A command facility for providing stationkeeping commands to a satellite in a substantially geosynchronous orbit characterizable by a line of antinodes, comprising:

• a processor implementing instructions to generate commands to perform a program of satellite control maneuvers at times and in directions to apply substantially all eccentricity control (Δeman) along the line of antinodes such that an argument of perigee of the satellite orbit during the at least one year changes by greater than 180 degrees if the program of control maneuvers are performed for at least one year;
• and
• a transmitter, communicatively coupled to the processor to transmit the command to the satellite.

A method of controlling an eccentricity of a satellite orbit characterizable by a line of antinodes while simultaneously controlling an eccentricity of the orbit, comprising the step of:

• performing a program of control maneuvers at a time and in a direction to apply substantially all eccentricity control (Δeman) along the line of antinodes;
• and
• wherein an angle between an in-orbital plane component of the control maneuver and an in-orbital plane component of a line projected from the satellite to the sun is at least 30 degrees.