Tracking control for cislunar spacecraft asymptotic fly-around

DOI编号  10.7641/CTA.2018.80103
2018,35(10):1458-1463

 作者 单位 E-mail 王毓媛 国防科技大学 wyy15nudt@sina.com 白玉铸 国防科技大学 baiyuzhu@hotmail.com 许展鹏 国防科技大学 赵勇 国防科技大学 陈小前 国防科技大学

在圆形限制性三体问题的框架下研究了地月空间航天器绕飞接近跟踪控制方法. 首先,以圆形限制性三体问题为基础建立了地月空间航天器相对运动模型, 并通过量纲化和线性化方法对模型进行了简化. 接着, 将地月空间航天器绕飞接近跟踪控制问题转化为模型参考输出跟踪问题, 并结合模型参考输出跟踪理论和线性二次型最优控制理论设计绕飞接近跟踪控制器. 最后, 通过数学仿真验证控制器的有效性和可行性, 仿真结果表明该方法能够实现地月空间航天器绕飞接近跟踪控制, 对位置和速度的初始状态误差能够快速收敛.

This paper investigates the tracking control problem on cislunar spacecraft asymptotic fly-around, in the framework of circular restricted three-body problem. Firstly, based on the circular restricted three-body formation dynamics, the model of relative motion for cislunar spacecraft formation is developed, and the it is simplified by way of normalization and linearization soon afterwards. Then, the problem of asymptotic fly-around control is transformed into the problem of tracking the reference trajectory, and the controller is developed to achieve the problem according to the model reference output tracking theory and linear quadratic optimal theory. Finally, a numerical simulation is carried out to indicate that the method is effective; the results show that the proposed controller can realize asymptotic fly-around tracking control for deputy spacecraft in cislunar space, and the initial error of position and velocity can be converged rapidly.