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首页> 外文期刊>Journal of guidance, control, and dynamics >Approach Guidance with Double-Line-of-Sight-Measuring Navigation Constraint for Autonomous Rendezvous
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Approach Guidance with Double-Line-of-Sight-Measuring Navigation Constraint for Autonomous Rendezvous

机译：自主交会的双视线导航约束进近制导

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摘要

Based on double-line-of-sight measuring relative navigation method, an approach guidance law with the triangle-measuring constraint is presented for autonomous rendezvous. The observability of double-line-of-sight measuring relative navigation system is analyzed using the state estimation error covariance matrix. The triangle-measuring navigation constraint is described as a keep-out cone. The approach guidance law is designed via artificial potential function method. It is ensured that there is a high region of potential in the keep-out cone and the potential still has a unique minimum at the goal position. Numerical simulations are undertaken to verify the guidance method proposed. The results indicate that the control impulses of the potential function guidance ensure convergence of the chase spacecraft to reach the goal position without violating the navigation keep-out zone.
机译：基于双视线测量相对导航方法，提出了具有三角测量约束的自主会合进近制导律。使用状态估计误差协方差矩阵分析了双视线测量相对导航系统的可观察性。测量三角形的导航约束称为保持锥。逼近制导律是通过人工势函数法设计的。确保保持锥中有较高的电势区域，并且在目标位置电势仍具有唯一的最小值。进行了数值模拟，以验证所提出的制导方法。结果表明，潜在功能制导的控制脉冲可确保追赶航天器在不违反导航避让区的情况下收敛到目标位置。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2011年第3期|p.678-687|共10页
  • 作者

    Tong Chen; Shijie Xu;

  • 作者单位

    Beijing University of Aeronautics and Astronautics, 100191 Beijing, People's Republic of China,Department of Guidance, Navigationand Control;

    Beijing University of Aeronautics and Astronautics, 100191 Beijing, People's Republic of China,School of Astronautics, Department of Guidance, Navigation and Control;

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