Attitude Control of Spacecraft Formation under Directional Constraints

In order to solve the problem of large-angle and high-precision reorientation of spacecraft under external directional constraints, a spacecraft attitude control method is proposed. Firstly, a strictly lower convex logarithmic boundary potential function is designed based on the formation member’s attitude; then a new sliding mode surface is designed to meet the attitude and the angular velocity amplitude constraints, and the switching strategy of intermediate variables is proposed based on the existence condition of the repulsive potential function, and then the adaptive coordination tracking controller under the saturation of the actuator is designed. Finally, the effectiveness of the design is verified by simulation analysis.