Inclination vector control with continuous or quasi-continuous maneuvers

1. A satellite inclination control method comprising:

tracking inclination vector cycles for a satellite in near geosynchronous orbit; and

performing a plurality of thruster firings of quasi-continuous inclination deltas each day over several days to counter growth of the inclination vector cycles;

wherein the quasi-continuous inclination deltas ensure that an osculating inclination vector of the satellite is centered on an ideal continuously controlled osculating trajectory between episodic inclination maneuver deltas;

the quasi-continuous inclination deltas from each thruster firing providing an approximation to a continuous inclination vector control rate; and

wherein the quasi-continuous inclination deltas provide a closed loop feedback control in which a maneuvering delta is determined over a first interval, and only a solution over a sub-interval of the first interval is retained for a quasi-continuous intra-maneuvering trajectory.

2. The method of claim 1 , wherein the plurality of thruster firings comprises ΔV firings of ion thrusters.

3. The method of claim 1 , wherein performing a plurality of thruster firings of quasi-continuous inclination deltas comprises

applying only the inclination deltas which counter a secular perturbation of inclination.

4. A satellite inclination control method comprising:

tracking inclination vector cycles for a satellite in near geosynchronous orbit; and

performing a plurality of thruster firings of quasi-continuous inclination deltas each day over several days to counter growth of the inclination vector cycles according to a control function having a predetermined minimum fuel target;

the control function controlling only secular Saros perturbations while leaving a biannual solar cycle uncontrolled to minimize fuel use.

5. The method of claim 4 , wherein the minimum fuel target locus which minimizes the fuel use is a circle of radius 22.5 mdeg.

6. The method of claim 1 , wherein the continuous inclination vector control rate is applied to control the osculating inclination vector to converge in mean to a desired inclination vector target locus.