中文摘要：

针对编队飞行航天器姿轨耦合一体化控制问题,本文提出了一种高精度快速收敛的滑模控制方法。首先,建立了以Lie群SE（3）上指数坐标表示航天器位置和姿态跟踪误差的相对耦合动力学模型。然后以该指数坐标和速度跟踪误差定义的滑模面,设计了一种新型的基于切比雪夫神经网络（CNN）的非奇异快速终端滑模控制器（NFTSMC）,实现了跟踪航天器对目标航天器的有限时间跟踪控制,并基于Lyapunov方法证明了系统的稳定性。该控制器无需显式的相对参考状态,不仅能保证滑模到达阶段和滑动阶段的有限时间稳定性,还由于引入仅需期望信号具有强逼近能力的CNN在线自适应估计系统总扰动而获得了较高的控制精度。最后,对主从模式的编队飞行航天器进行了仿真分析,结果表明该方法是有效可行的。

英文摘要：

A sliding mode control scheme with high accuracy and fast convergence is proposed to solve the coupled- control problem of a spacecraft formation flying system in this paper. First,in the presence of structured and unstructured uncertainties,coupled dynamics model of relative position and attitude are derived based on the Lie group SE（ 3）,in which the tracking errors of position and attitude are described by exponential coordinates on SE（ 3）. A new nonsingular fast terminal sliding mode controller（ NFTSMC） based on Chebyshev neural network（ CNN） is proposed to make the tracking control come true in finite time by using a sliding surface,which is defined by the exponential coordinates and velocity tracking errors,and the stability of the closed- loop system is proved by Lyapunov methods. The controller doesn＇t need explicit reference states and can guarantee finite-time stability in both the reaching phase and the sliding phase. Since the adaptive control scheme based on CNN,whose basis functions only need the expected signals and represented capabilities is powerful,is introduced to approximate the total disturbance online,the controller also has high accuracy. Finally,numerical simulations on the leader-follower spacecraft formation are presented to validate the effectiveness and feasibility of the proposed controller.