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Optimal Impact Angle Control Guidance Law Based on Linearization About Collision Triangle

机译:基于碰撞三角形线性化的最佳冲击角控制制导律

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摘要

In this Note, a new impact angle control optimal guidance law has been developed for missiles with arbitrary velocity profiles against maneuvering targets. The guidance law development is based on the linearization of kinematics around the zero-effort collision triangle, which has been newly introduced for impact angle control problems and behaves like an equilibrium point in the engagement dynamic system. The best guidance performance has been shown in a numerical simulation work when the reference line is chosen in such a way that the distance between the current missile position and the corresponding vertex of the zero-effort collision triangle is fully captured by a guidance variable. Many important practical questions such as how it performs under the presence of uncertainty in the information of future target maneuver and missile velocity profile remain to be addressed.
机译:在本说明中,针对具有任意速度轮廓的机动目标,已经开发了一种新的撞击角控制最佳制导律。制导律的发展基于零努力碰撞三角形周围的运动学线性化,该运动学是针对碰撞角控制问题而新引入的,其行为类似于接合动态系统中的平衡点。当选择参考线时,数值模拟工作显示出最佳的制导性能,以这种方式,制导变量可完全捕获当前导弹位置与零努力碰撞三角形的相应顶点之间的距离。许多重要的实际问题,例如在未来目标机动信息和导弹速度分布信息中存在不确定性的情况下其性能如何,还有待解决。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2014年第3期|958-964|共7页
  • 作者单位

    Hanwha Corporation Research and Development Center, Daejeon 305-156, Republic of Korea;

    Inha University, Incheon 402-751, Republic of Korea;

    Cranfield University, Shrivenham, England SN6 8LA, United Kingdom;

    Cranfield University, Shrivenham, England SN6 8LA, United Kingdom;

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  • 正文语种 eng
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