中文摘要：

飞行器在轨精度跟踪优化问题,根据在轨服务任务需求,针对非合作翻滚目标航天器的自主接近跟踪问题,首先从采用视线坐标系表示的轨道动力学方程和修正罗德里格斯参数表示的姿态动力学方程出发,建立了航天器六自由度类拉格朗日动力学方程;然后仅利用相对位置和相对姿态反馈信息并针对航天器惯性参数不确定性,采用自适应非线性输出反馈控制和神经网络逼近控制方法设计了姿轨联合控制器,并通过Lyapunov直接法证明了该闭环系统的全局渐进稳定性;最后通过仿真验证了采用的方法能够实现对非合作目标的精确跟踪.

英文摘要：

This paper investigated the requirement of the on-orbital service in the future,which is how to approach the non-cooperative object in a autonomous way.Firstly,based on the orbit dynamics equation described in the line-of-sight coordinate frame and the attitude dynamics equation described with the Modified Rodriques Parameters in the body coordinate frame of the chaser spacecraft,the spacecraft＇ s six degrees of freedom quasi-Lagrange dynamics equation was set up.And then,only using the relative position and the relative attitude information,and also considering the uncertainty of the spacecraft quality,the adaptive non-linear output feedback control and the neural networks control were employed to design the combined attitude and orbit controller.In order to prove the closed loop system＇ s stability,the Lyapunov approach was used.Finally,the simulation results confirmed the validity of the method which can achieve the good tracking performance when approaching to the target.