Autonomous relay control system for satellite formation operating in low Earth orbit
A relay control algorithm is proposed for the satellite formation consisting of a «passive» (virtual) spacecraft moving in an unperturbed circular orbit, and several «active» spacecraft maneuvering relative to it. The purpose of control is to keep each active spacecraft on its finite path relative to the virtual spacecraft defining the center of formation with as low as possible propellant consumption. To describe the motion of maneuvering spacecraft relative to the center of formation, modified Hill-Clohessy-Wiltshire equations are used accounting for the earth’s flattening and aerodynamic drag. The main emphasis of this paper is on the study of the existence of stable limit cycles and determination of their domains of attraction, as well as the search for values of the relay control system parameters ensuring a minimum propellant consumption for maintaining a proper dynamic formation behavior.