Nonlinear Earth orbit control using low-thrust propulsion

This research is focused on the definition, analysis, and numerical testing of an effective nonlinear orbit control technique tailored to compensating perturbations, as well possible errors at injection low- medium-altitude Earth-orbit satellites. A general, systematic approach real-time presented, under assumption that satellite interest equipped with a steerable throttleable low-thrust propulsion system. Two different operational orbits are considered: (a) very-low-altitude Earth (b) orbit. feedback law based Lyapunov stability theory proposed tested. Some remarkable properties established analytically. Then, overall performance hand investigated for cases (b), over 5 years. The effect eclipsing available electrical power considered well. For mission scenario (a), suitable tolerances desired (nominal) conditions allow substantial savings in terms propellant requirements.