Research on Integrated Touchless Control Technology Based on Inter-Satellite Electromagnetic Force

Propellant consumption is the main factor limiting the service life of spacecraft in orbit. A spacecraft that runs out of fuel will lose its orbital maneuverability. Whether it is an effective spacecraft or a space debris, it needs external force to control its orbit. Traditional contact control methods, including mechanical arm capture, rope capture, etc., are at risk of collision and lack versatility. This paper proposes an integrated touchless orbit control scheme for spacecraft with electromagnetic coils and no inertial thrust. The active spacecraft with inertial thrust and electromagnetic coils is used to carry out touchless control of the target spacecraft. The inertial thrust changes the centroid motion of spacecraft formation. Electromagnetic force/torque keeps the relative position and relative attitude of spacecraft formation. Sliding mode control law is designed for inertial thrust to achieve the target satellite orbit control while maintaining the formation configuration. To reduce the accumulation of angular momentum caused by the geomagnetic field, an angular momentum management program based on current control was adopted, and the feasibility of the designed control program was verified through simulation calculations. It provides new ideas for the orbit correction of spacecraft and the de-orbit of failed spacecraft.