Implementation of autonomous GPS guidance and control for the spacecraft formation flying

This paper presents the general relative orbit dynamics equations and GPS orbit observational equations that have been developed for on-board control of spacecraft flying in formation. The approach to the implementation of the autonomous control for orbit acquisition maintenance of spacecraft formation using GPS code pseudo-ranges are presented. The orbit control of the Earth-Orbiter 1 (EO-1)/Landsat 7 system has been designed, using the discrete-time linear optimal output feedback control. For the actuator of the on/off type reaction jets, the implementation problem of the pulse-amplitude modulation is also studied. Simulation results of autonomous orbit control and maintenance, for 3D initial orbit error, using optimal output feedback control are shown. These simulation results certified the feasibility of the implementation of the autonomous maintenance control for EO-1/Landsat 7 formation flying by means of the discrete-time linear optimal output feedback control.