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This study is concerned with the spacecraft close-range attitude tracking control system with parameter uncertainty and external disturbances. First, an extended state observer is employed to estimate and compensate for the rotational inertia uncertainty and external disturbances. Second, based on the integral terminal sliding mode surface, the attitude tracking control law with unmeasured angular velocity is proposed which guarantee the attitude control system asymptotically stable. Finally, through the simulation results, the effectiveness of the proposed control law is demonstrated.
Lin et al. (Fri,) studied this question.
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