This paper provides a new solution for the finite‐time attitude maneuvers of rigid spacecraft. Uncertainties involving unknown inertial parameters, external disturbances and actuator failures are taken into account. With an effort to achieve attitude tracking despite the impact of uncertainties, a non‐singular terminal sliding mode (NTSM) manifold consisting of attitude errors and angular velocity errors is first constructed. After that, a simple but efficient adaptive updating law is derived to estimate the upper bound of the lumped unknown function in the derivative of sliding surface. Combining NTSM technology and pure adaptive control, a chattering‐free fault‐tolerant controller is presented. The premise assumptions on uncertainties in most of the existing achievements are eliminated, which makes the controller less constrained and more practical. The rigorous proof of finite‐time stability is provided and the convergent regions of tracking errors are explicitly expressed. Finally, numerical simulation is conducted to verify the effectiveness of the proposed control scheme and the comparison experiments with relevant literature demonstrate the satisfactory performances.

中文翻译：

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刚性航天器姿态跟踪的有限时间自适应容错控制

本文为刚性航天器的有限时间姿态机动提供了一种新的解决方案。考虑了涉及未知惯性参数，外部干扰和执行器故障的不确定性。为了在不受不确定性影响的情况下实现姿态跟踪，首先构造了一个由姿态误差和角速度误差组成的非奇异终端滑模（NTSM）歧管。此后，推导了一个简单而有效的自适应更新定律，以估计滑动面导数中集总未知函数的上限。结合NTSM技术和纯自适应控制，提出了一种无抖动的容错控制器。消除了大多数现有成就中不确定性的前提假设，这使得控制器的约束更少，更实用。提供了有限时间稳定性的严格证明，并明确表示了跟踪误差的收敛区域。最后，进行了数值模拟，验证了所提控制方案的有效性。与相关文献的对比实验表明，该方法具有令人满意的性能。