Intercept-Angle Guidance
Intercept-Angle Guidance
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DOI：
10.2514/1.51026
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发表时间：
2011-03
影响因子：
2.6
通讯作者：
T. Shima
中科院分区：
文献类型：
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作者：
T. Shima
感兴趣是导弹和机动目标之间的空中拦截。制导概念适用于所有的空中拦截几何形状：即，迎头拦截、尾随拦截和新式的迎头追击。这些不同的啮合几何形状的存在的分析条件。的指导思想是使用滑模方法。该制导律不采用通常的初始碰撞三角形假设，因而对中末制导都适用。通过仿真研究了该方法在不同啮合几何条件下的应用。结果表明，在迎头拦截情况下，拦截角的变化范围最小，对拦截弹的机动能力要求最高，因此，在某些情况下，应考虑采用尾随或迎头追击的方式。两者之间的选择取决于对手的速度比;对于尾追，拦截器必须比目标具有速度优势，而对于头追，它必须具有速度劣势。
interest is aerial interception between a missile and a maneuvering target. The guidance concept is applicable in all aerial interception geometries: namely, head-on, tail-chase, and the novel head-pursuit. Analytical conditions for existence of these different engagement geometries are derived. The guidance concept is implemented using the sliding-modeapproach. Thecommonassumption of flight alonganinitial collisiontriangle isnottaken,andthusthe guidance law is applicable for both midcourse and endgame guidance. The application in the different engagement geometries is studied via simulation. It is shown that the head-on scenario allows the smallest range of intercept angles.Italsoplacesthemostseveremaneuverabilityrequirementsontheinterceptor.Thus,insomecases,tail-chase or head-pursuit engagements should be considered instead. The choice between the two is dependent on the adversary’s speed ratio; for tail-chase, the interceptor must have a speed advantage over its target, while for headpursuit, it must have a speed disadvantage.