空空导弹末端制导变结构导引律研究

 空空导弹末端控制(Endgame)段适用的导引规律,必须确保在目标实施最佳逃逸策略时,导弹以最小的脱靶量命中它。由于目标机动特性较难掌握,为了提高导弹的命中精度,在实际工程设计中,要求导弹飞行控制系统具有更高的机动过载和更小的时间常数。而直接力控制技术的引入,可明显提高导弹最大可用过载,减小导弹飞控系统时间常数。本文以比例导引律为基础,将目标机动视为未知的有界干扰,设计一种变结构导引律,利用变结构控制系统的干扰不变特性,克服目标机动的影响,实现目标有界机动条件下视线角速度的零化,使导弹飞行弹道在制导过程的中后段呈现出平行接近法的特性,以改善导弹制导性能。经对制导回路进行稳定性分析,对具有直接力控制与不具有直接力控制的制导系统分别进行仿真分析,表明在Endgame中,变结构导引律比一般的比例导引律脱靶量更小,引入直接力控制后效果更为明显。

Research on Variable Structure Guidance Law of Air-to-Air Missile in Endgame

The suitable guidance law of air-to-air in Endgame must ensure that the missile with the minimum miss-distance hits the target implementing best escape strategy. Because the characteristic of maneuverable target is hard to be mastered, and in order to improve the hit accuracy of missile, it required the higher motor overload and the smaller time constant of missile flight control system in practical design of engineering. Thus introduce of reaction-jet control can obviously improve the missile maximum available overload, and reduce the time constant of missile flight control system. In this paper a variable structure guidance law is designed based on the proportional guidance law. Variable structure control system can provide the same features to overcome the influence of target maneuver, and achieve the goal of zero under the bounded maneuvering condition of LOS angular velocity, which made the ballistic flight to show the characteristics of parallel approaching method in the missile-after guidance process, and then it can improve the missile guidance performance. Analysis of the guidance loop on the stability and simulation analysis of the guidance system with or without the reaction-jet controller demonstrated that the miss-distance of the variable structure guidance law is smaller than PNG and the effect is better with reaction-jet controller.