导弹末端机动与导引一体化设计的新机动模型  

A New Maneuver Model for Integrated Design of Missiles' Terminal Maneuver and Guidance

作　　者：秦建飞[1] 张义广[1] 李俊峰[2] 

机构地区：[1]中国航天科工集团第九总体设计部,武汉430035 [2]清华大学航天航空学院,北京100084

出　　处：《宇航学报》2009年第5期1866-1870,共5页Journal of Astronautics

摘　　要：针对导弹末端机动与导引的一体化设计问题,给出了一种新的机动模型。通过模型参数的设计,使得机动位移、机动速度的零点周期性地出现在相同的时刻,导弹就可以在导引弹道和机动导弹之间平滑过渡。基于该模型,采用导引弹道和机动弹道同步积分的方法,选择合适的时刻开始和结束机动,可以实现末端机动与导引的一体化设计。该方法得到的一体化弹道,其制导精度仅取决于末制导律,而与具体的机动参数无关,具有较好的突防效果和工程应用价值。A new maneuver model is presented with respect to integrated design of maneuver and guidance of terminal phase for missiles. When its model parameters are chosen properly, the maneuver displacement and velocity turn zero at the same point periodically, which means the missile can switch between the guidance and maneuver trajectory smoothly. Thus in a way that the guidance and maneuver trajectory arc simultaneously calculated based on this model for the appropriate time to start and stop maneuvering, we can realize integrated design of maneuver and guidance of terminal phase. For the integration trajectory got, guidance accuracy is depended on the terminal guidance law only, instead of the maneuver parameters. As a result, this method demonstrates better anti-defense effect and practical value.

关 键 词：机动模型 末端机动 末制导 一体化设计 

分 类 号：V448[航空宇航科学与技术—飞行器设计]