This problem deals with maneuvering an inspector satellite relative to a leader satellite in a geosynchronous orbit around the Earth. For this specific problem, the satellite utilizes a unique method to accomplish these maneuvers. Typical satellites perform orbital maneuvering by means of conventional thrusters. While thrusters are a proven, reliable method for maneuvering a satellite, they will always lead to constraints on satellite lifetime. The current study explores a means of orbital maneuvering in which thrusters are replaced with a device capable of accomplishing the same maneuvers while increasing satellite lifetime. Specifically, instead of using thrusters, all of the propulsive force comes from a solar wing.
This analysis explores two separate maneuvers using solar radiation pressure as the propulsive force. The first maneuver that is examined is a point-to-point maneuver, simulating an inspector satellite performing an inspection on a leader in GEO. The second maneuver that is investigated is a station-keeping maneuver. In this case the goal is to keep the satellite within a certain tolerance in the along-track direction using solar pressure as the propulsive force.