Characteristic model-based large angle maneuver attitude control for spacecraft

In the paper, aiming at the large-angle attitude maneuver problem of the spacecraft of which the inertia matrix is uncertain, we establish the spacecraft's error quaternion attitude tracking model, and we use the golden section adaptive control method combined with the logic differential control method, following the planning path, to complete the large-angle attitude maneuver control of the spacecraft. By introducing generalized control, the input coefficient matrix can be approximated to a diagonal matrix, at the same time, the coupling condition of input and output coefficient matrix is analyzed. The simulation shows the coupling terms have little influence on the performance of control, but in the case of input-output decoupling, we can choose different controller parameters for three-axis to improve system performance.