Design of guidance law of missile in attack with high angle
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摘要: 针对导弹带落角约束条件的作战要求,基于Lyapunov稳定性原理设计了一种既能准确命中目标又能保证大落角的制导律.该制导律将末端角度约束转化为弹目视线角约束,其表达式包含两部分,分别是基于弹目视线角速度的反馈,及弹目视线角与期望视线角之差的反馈.通过合理地调节二者的比例关系,即可保证该制导律在可用过载范围内以期望的大落角击中目标.此制导律形式简单,便于工程实现.此外,充分考虑了导弹的机动性能和导引头特性,给出了末制导律引入时的最佳初始条件.通过某型导弹的弹道仿真,验证了该制导律的有效性.Abstract: According to the requirements of impact angle constraint of the missile, a new terminal guidance law was deduced base on the Lyapunov method to null miss distance and to achieve a desired impact attitude angle, simultaneously. The impact angle constraint was turned to line of sight angle constraint in this method. The proposed guidance law contains two parts that base on line of sight angle rate and the difference between the line of sight angle and the required line of sight angle, respectively. To adjust the two parts portion reasonably the guidance goal with the overload constraint can be realized. The proposed guidance law is simple and convenient to be realized in engineering. Besides that, the best initial condition when the guidance law imported was analyzed considering the missile-s overload availability and the seeker-s performance. The simulation result for model of some missiles shows the effectiveness of this proposed guidance law.
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Key words:
- terminal guidance /
- high impact angle /
- available overload
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