Cui Bing, Xia Yuanqing, Liu Kun, Zhang Jinhui, Wang Yujuan, Shen Ganghui
IEEE Trans Cybern. 2022 Jul;52(7):5882-5896. doi: 10.1109/TCYB.2020.3034645. Epub 2022 Jul 4.
This article addresses the finite-time attitude formation-containment control problem for networked uncertain rigid spacecraft under directed topology. A unified distributed finite-time attitude control framework, based on the sliding-mode control (SMC) principle, is developed. Different from the current state of the art, the proposed attitude control method is suitable for not only the leader spacecraft but also the follower spacecraft, and only the neighbor state information among spacecraft is required, allowing the resulting control scheme to be truly distributed. Furthermore, the proposed method is inherently continuous, which eliminates the undesired chattering problem. Such features are deemed favorable in practical spacecraft applications. In addition, upon using the proposed neuro-adaptive control technique, the attitude formation-containment deployment can be achieved in finite time with sufficient accuracy, despite the involvement of both the uncertain inertia matrices and external disturbances. The effectiveness of the developed control scheme is confirmed by numerical simulations.
本文研究了有向拓扑下网络化不确定刚体航天器的有限时间姿态形成-约束控制问题。基于滑模控制（SMC）原理，开发了一种统一的分布式有限时间姿态控制框架。与现有技术不同，所提出的姿态控制方法不仅适用于领航航天器，也适用于跟随航天器，并且只需要航天器之间的邻域状态信息，从而使所得到的控制方案真正具有分布式特性。此外，所提出的方法本质上是连续的，消除了不期望的抖振问题。这些特性在实际航天器应用中被认为是有利的。此外，使用所提出的神经自适应控制技术，尽管存在不确定的惯性矩阵和外部干扰，姿态形成-约束部署仍可在有限时间内以足够的精度实现。数值仿真验证了所开发控制方案的有效性。
