Integrated attitude control with momentum management for spacecraft electromagnetic docking

This paper concentrates on the design approaches of attitude control with momentum management, which is still a difficult and hot problem, especially for spacecraft electromagnetic docking technology. The integrated controller design frame is firstly brought forward, and sequence solutions with magnetic dipoles are provided. After the magnetic design, the extended state model of attitude control with momentum management is derived. Considering the magnitude, rate and bandwidth constraints of attitude control mechanism, as well as requirements of spacecraft docking mission, several approaches including linear, nonlinear and optimal methods for a single satellite or multiple satellites are studied. A simple simulation case is presented to verify the feasibility and performance of these approaches. At last, some conclusions are given.