地月空间航天器绕飞接近跟踪控制
Tracking control for cislunar spacecraft asymptotic fly-around
摘要点击 51  全文点击 47  投稿时间:2018-02-05  修订日期:2018-08-20
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DOI编号  10.7641/CTA.2018.80103
  2018,35(10):1458-1463
中文关键词  地月空间  绕飞  跟踪控制  模型参考  线性二次型调节器
英文关键词  cislunar  fly-around  tracking control  model reference  linear quadratic regulator (LQR)
基金项目  国家自然科学基金委重大项目(61690210, 61690213)资助.
学科分类代码  590.35
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  
中文摘要
      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.
英文摘要
      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.