Timeoptimized northsouth stationkeeping
Abstract
A control strategy for geosynchronous satellites is developed which produces a trajectory history with the maximum time between maneuvers and the minimum annual velocity change, leading to the optimum annual deltaV requirements. The solarlunar gravitational perturbations which give rise to the need for plane change maneuvers are first reviewed. The control strategy permits the inclination trajectory to have a magnitude less than or equal to the minimum measurable inclination somewhere near the middle of its path. It thus has the greatest arc length through the constraint circle. This technique also determines the minimum annual velocity change required.
 Publication:

Journal of Guidance Control Dynamics
 Pub Date:
 June 1983
 DOI:
 10.2514/3.19821
 Bibcode:
 1983JGCD....6..220G
 Keywords:

 Geosynchronous Orbits;
 Satellite Perturbation;
 Spacecraft Control;
 Stationkeeping;
 Time Optimal Control;
 Trajectory Optimization;
 Gravitational Effects;
 Optimization;
 Spacecraft Maneuvers;
 Astrodynamics