| 摘 要： |
To improve the penetration probability of missiles against air defense systems and enhance the lethal effect of the warhead on the target, a climb-and-dive guidance law, which satisfies the altitude constraint subject to the impact angle constraint, is proposed in this paper. First, the altitude of the trajectory is shaped as a nicely designed function with respect to the cross range in rectangular coordinates. Then, the guidance command is obtained inversely by calculating the curvature radius from the trajectory equation. In addition, the maximum altitude of the trajectory can be simply adjusted by a guidance parameter. Moreover, to guarantee the precision of the guidance, the widely used closed-loop guidance law is developed. Compared with some published guidance laws that can address the impact angle control problem, a noticeable superiority of the proposed guidance law is the ability to control the altitude under the impact angle constraint. The validity and merits of the proposed climb-and-dive guidance law are verified through a series of numerical simulations.
为提高导弹对防空系统的穿透概率，并增强弹头对目标的杀伤效果，本文提出了一种满足撞击角约束条件下的爬升-俯冲制导律，该律同时满足高度限制要求。首先，将轨迹的高度在直角坐标系中设计为与横跨距离相关的良好函数形式；其次，通过计算轨迹方程的曲率半径，反向求得制导指令。此外，可通过调整一个制导参数简单地调节轨迹的最大高度。为了确保制导精度，还开发了广泛应用的闭环制导律。与一些已发表的能够解决撞击角控制问题的制导律相比，所提出的制导律显著优势在于能够在撞击角约束条件下控制飞行高度。通过一系列数值仿真验证了该爬升-俯冲制导律的有效性与优点。 |
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