Proximity Hovering Orbital Dynamic Model and Control Method for Spacecraft

In this study the proximity hovering orbital dynamic model and control method are investigated. This dynamic model, constructed on the orbit elements, gives the relative motion between the chief satellite and the deputy satellite in the space. The continuous closed-loop orbital control law is developed based on the dynamic model, which means that through continuous limited thrust control the deputy satellite would transfer into a new maneuvering orbit, not the natural Kepler orbit. The simulation result shows the effectiveness of this dynamic model and the control law. The deputy satellite can proximity hover around the chief satellite with a little energy consume (3.79 m/s velocity increment) when the desired radial distance is 500 m during one orbit period.