The finite-time attitude stabilization of spacecraft subject to actuator constraints and attitude measurements only is investigated. A saturated output feedback finite-time proportional-derivative control is proposed. Lyapunov stability theory and homogeneous method are employed to show the finite-time stabilization. Advantages of the proposed control include the finite-time stabilization featuring faster transient and higher precision and the absence of the modelling information and the velocity measurements in the control law formulation, and thus, it offers an easy-going solution for high-quality motion control of spacecraft. An additive feature is that the actuator saturation will not be reached by selecting the control gains a priori. Simulations are presented to illustrate the effectiveness of the proposed control.

中文翻译：

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航天器有限时间姿态稳定的饱和输出反馈控制

仅研究受致动器约束和姿态测量的航天器的有限时间姿态稳定。提出了一种饱和输出反馈有限时间比例微分控制。采用Lyapunov稳定性理论和齐次方法证明了有限时间镇定。所提出的控制的优点包括有限时间稳定，具有更快的瞬态和更高的精度，并且在控制律公式中没有建模信息和速度测量，因此，它为高质量的运动控制提供了一个简单的解决方案的航天器。附加特征是通过先验选择控制增益不会达到致动器饱和。提出了模拟来说明所提出的控制的有效性。