Integrated Attitude and Orbit Control of Spacecraft in Asteroid Soft Landing

This paper mainly studies the integrated attitude and orbit control of spacecraft under external interference when landing asteroid. Firstly, assuming that only one orbital engine is equipped on the spacecraft, based on the relative orbital dynamic model expressed in the landing point coordinate system and relative attitude dynamics model expressed in the system of proprio-coordinate, an integrated attitude and orbit dynamic model is established. Secondly, based on the filtering Backstepping idea, the nonlinear part of the integrated attitude and orbit model is transformed, the integrated attitude-orbit control law with certain disturbance suppression ability is designed, and the stability analysis of the closed-loop system is given. Finally, the proposed control scheme is simulated by numerical simulation, and compared with the traditional separated attitude and orbit control, the effectiveness and superiority of the integrated attitude and orbit control are verified.