Collision-Avoidance Maneuver of Satellites Using Drag and Solar Radiation Pressure

This paper discusses the feasibility of using drag and solar radiation pressure for a collision-avoidance maneuver. Usually, an alert about possible collision with another satellite or space debris is received a few days in advance, giving ample time to design and perform an avoidance maneuver. For a propulsionless satellite, drag and solar radiation pressure are the only natural forces that can be used for orbit maneuver. The maneuver is performed by orienting the satellite such that the combined effect of both forces will add up to maximize the change of the semimajor axis from the nonmaneuver case. This causes a change in the orbital period, and eventually, after enough revolutions, the satellite avoids the collision. The control algorithm requires the knowledge of the cross-section areas of the satellite from all directions as well as the drag and solar radiation properties. There must be a difference between the maximum cross-section area and the minimum one to control these natural forces. Numerical examples for a real satellite show that the method is feasible. The along-track deviation that is accumulated after no more than three days of maneuver is sufficient to reduce the collision probability to acceptable level.