In this paper, a bounded finite-time control strategy is developed for the final proximity maneuver of spacecraft rendezvous and docking exposed to external disturbance and input quantization. To realize the integrated control for spacecraft final proximity operation, the coupling kinematics and dynamics of attitude and position are modeled by feat of Lie group . With a view to improving the convergence rate and reducing the chattering, an adaptive finite-time controller is proposed for the error tracking system with one-step theoretical proof of stability. Meanwhile, the hysteresis logarithmic quantizer is implemented to effectively reduce the frequency of data transmission and the quantization errors are reduced under the proposed controller. The algorithms outlined above are based on an integrated model expressed by and denoted by uniform motion states, which can simplify the design progress and improve control precision. Finally, simulations are provided to exhibit the effectiveness and advantages of the designed strategy.

中文翻译：

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具有输入量化的航天器最终接近机动的 SE(3) 自适应有限时间控制

在本文中，为暴露于外部干扰和输入量化的航天器交会对接的最终接近机动开发了一种有界有限时间控制策略。为实现航天器最后接近运行的集成控制，利用李群的壮举对姿态和位置的耦合运动学和动力学建模。为了提高收敛速度和减少抖动，提出了一种具有一步稳定性理论证明的误差跟踪系统的自适应有限时间控制器。同时，在所提出的控制器下，实现了滞后对数量化器以有效降低数据传输频率并减少量化误差。上述算法基于由匀速运动状态表示和表示的集成模型，可以简化设计过程并提高控制精度。最后，提供了模拟以展示所设计策略的有效性和优势。