Abstract: A satellite formation maneuver control using model predictive control method was presented. When satellites within a formation are of different geometry and mass, drag and J₂ become the most important perturbations affecting the satellite formation. The relative dynamics including the effects caused by the drag and J₂was developed using the relative mean orbit element. A new control method, model predictive control, was applied to the satellite formation maneuver control. This control is an online optimization and effective control method to deal with multivariable constrained control even that the control process exits different disturbances. Simulation results show that this control method is near fuel optimal and it can control the satellite formation to the desired formation within the error box.

Key words: control and navigation technology of aerocraft, satellite formation, formation maneuver, model predictive control, relative orbit element