Abstract: In order to solve the problems of low efficiency and no guarantee of approaching safety in the eddy current detumbling task of space tumbling targets, direct linearization convex safety constraints for the maneuver trajectory of the servicer satellite are given based on the ellipsoid envelope method, to ensure the safety of maneuvering process and the finite time solvability of optimal tracking problems. The desired approaching trajectory in perpendicular configuration is designed to enhance the detumbling effect of the servicer satellite and shorten the task period. On this basis, a feedback linearization contractive model predictive control(FLC MPC) algorithm is proposed to effectively track the proposed desired trajectory and strictly guarantees the stability of the controlled system under safety and input constraints. Finally, the proposed control method is used to simulate detumbling of the Ariane 4 launch vehicle upper stage. The simulation results show that the proposed method can effectively improve the detumbling efficiency and ensure the safety and stability of the servicer satellite.

Key words: Space tumbling target, Eddy current detumbling, Safety constraint, Feedback linearization, Model predictive control