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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets
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Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets

机译：带有航空鳍和反应喷气机的拦截导弹的有界差分博弈制导律

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摘要

A differential game guidance law for an endoatmospheric interceptor missile steered by aero fins and reaction jets is developed in this paper with bounded controls. For a low-altitude endoatmospheric interceptor, the propellant of the reaction-jet control system (RCS) is restricted by the missile configuration. Considering propellant limits, the effect of the RCS thrust on homing performance is investigated through game space structures. Also, to use the RCS at an appropriate timing, game space decomposition is used to determine the initiating time of the RCS. Finally, the effectiveness of the guidance law is demonstrated by a realistic ballistic missile defense scenario. It is shown that the proposed guidance law provides a significant improvement in homing accuracy compared to the conditional one. Furthermore, under propellant limits, a bigger RCS thrust cannot guarantee a higher homing accuracy.
机译：本文利用有限的控制方法，开发了一种由气翅和反作用射流操纵的内大气层拦截弹的差分博弈制导律。对于低空大气层拦截器，反作用喷射控制系统（RCS）的推进剂受导弹构型的限制。考虑到推进剂极限，通过游戏空间结构研究了RCS推力对归巢性能的影响。同样，为了在适当的时机使用RCS，使用游戏空间分解来确定RCS的启动时间。最后，现实的弹道导弹防御方案证明了制导法的有效性。结果表明，与有条件的导引法则相比，所提出的导引法则在归位精度上有显着提高。此外，在推进剂极限下，更大的RCS推力不能保证更高的归位精度。

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