An investigation of on-orbit release with inter-satellite electromagnetic force

On-orbit release by inter-satellite electromagnetic force is a novel and valued technology characterized by repetitious release capability, release and re-docking operation integration, no propellant consuming and contamination, etc., thus it ensures a broad prospect of application in future routine on-orbit servicing missions. However, the related issues of dynamics characteristics and guidance control haven't been studied so far. This paper reveals the dynamics characteristics of relative trajectory motion of the “Partner” with respect to its “Master” and presents the principles and guidance control approach for the pre-designed elliptical orbit configuration. The cyclic pursuit theory is utilized to design this guidance controller and its pursuit strategy is designed. In addition, the parameters of the cyclic pursuit controller are tuned in accordance with the requirements of the specific pre-designed elliptical relative motion. The feasibility and performance of the guidance controller are verified by simulation results.