Abstract This paper studies the problem of attitude stabilization for a rigid spacecraft subject to external disturbances, time-varying inertia uncertainties, and input magnitude and rate constraints (MRCs). By analyzing the influence of inertia uncertainties, the reconstruction of lumped disturbances is accomplished to facilitate the controller design. Then, a disturbance observer is designed, based on which, a simple state feedback control strategy including estimation of lumped disturbances is proposed. By choosing new state variables using attitude information and estimation errors, an augmented plant is constructed. Using standard Lyapunov stability analysis, which shows that all states are uniformly ultimately bounded, sufficient conditions for the existence of the disturbance observer and controller are given based on linear matrix inequalities (LMIs). It is worth pointing out that the observer and controller gains are obtained simultaneously. It is shown that the control scheme developed is not only robust against external disturbances and unknown time-varying inertia uncertainties, but also able to steer the attitude control performance and estimation errors of lumped disturbances. Numerical simulations are performed to demonstrate the effectiveness of the proposed control strategy.

中文翻译：

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基于扰动观测器的刚性航天器姿态稳定输入 MRC

摘要 本文研究了受外部扰动、时变惯性不确定性和输入幅度和速率约束（MRCs）影响的刚性航天器的姿态稳定问题。通过分析惯性不确定性的影响，完成集中扰动的重构，以方便控制器设计。然后，设计了扰动观测器，并在此基础上提出了一种包括集中扰动估计的简单状态反馈控制策略。通过使用姿态信息和估计误差选择新的状态变量，构建了一个增强的植物。使用标准的 Lyapunov 稳定性分析，它表明所有状态最终一致有界，基于线性矩阵不等式（LMI）给出了干扰观测器和控制器存在的充分条件。值得指出的是，观测器和控制器的增益是同时获得的。结果表明，所开发的控制方案不仅对外部扰动和未知的时变惯性不确定性具有鲁棒性，而且能够引导姿态控制性能和集中扰动的估计误差。进行数值模拟以证明所提出的控制策略的有效性。但也能够引导姿态控制性能和集中扰动的估计误差。进行数值模拟以证明所提出的控制策略的有效性。但也能够引导姿态控制性能和集中扰动的估计误差。进行数值模拟以证明所提出的控制策略的有效性。