Rigid Spacecraft Attitude Control Based on Finite‐Time Non‐Singular Sliding Mode and Extended State Disturbance Observer With Input Hysteresis

ABSTRACT This paper investigates an adaptive finite‐time non‐singular terminal sliding mode control method (AFNTSMC) for a rigid spacecraft rapid attitude maneuver control. Meanwhile, the spacecraft suffer from adverse challenges such as input hysteresis, external disturbances, and system uncertainty. To estimate the lumped disadvantage disturbances, an extended state disturbance observer (ESDO) is applied, the ESDO can track the disturbance quickly and accurately. To mitigate the effects of residuals, an adaptive law is applied. Lyapunov theory is applied to confirm the stability of the attitude control system. To validate the efficacy of the proposed control law, comparison simulations are conducted. According to this spacecraft attitude maneuvering system, the results show that the designed AFNTSMC can drive the attitude to the target position rapidly. It can save more than 5 s, the steady‐state error is reduced by more than in steady stage.