Orbit transfer with a variable thrust Hall thruster under drag

The performance capabilities of an experimental Hall thruster were obtained experimentally for both variable and constant thrust modes at low power le vels in order to enable orbit transfer under the influence of air drag with small satellites. For this purpose the measured thruster performance was e mployed in calculations of transfer trajectories. As a result, by applying optimal thrust acceleration control the required propellant mass for a give n low-Earth-orbit transfer was reduced by 15-17% as compared to that requir ed for spacecraft operation with a constant thrust to power ratio. For this purpose a Hall thruster with a movable anode is needed. In addition, the o peration of an array of thrusters enables the increase of a factor of varia tions of the thrust acceleration during the Eight time.