小天体撞击末段脉冲比例制导律研究  

End-Stage Guidance for Impacting Small Asteroids Using Pulsed Proportional Guidance Law

作　　者：周卫文[1] 梁晓庚[1] 贾晓洪[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《电光与控制》2011年第6期69-73,共5页Electronics Optics & Control

摘　　要：考虑到机动时机的选取以及最终撞击的精度,针对小天体高速撞击任务的特点,设计了一种脉冲比例制导的末段制导律。该制导律引入点位误差椭圆来描述导航精度,并基于深空撞击器离散脉冲控制力的特点,以零控脱靶量落入误差椭圆的范围来控制轨控发动机的开关。通过严格的蒙特卡罗仿真表明,该制导律在节省燃料的同时,可以提高最终的撞击精度。A pulsed-proportional-guidance law was designed for impacting small celestial bodies such as asteroids and comets,which taking appropriate time selecting of trajectory maneuvering and final impacting precision into account.The precision of navigation system was given by using error ellipse,which is a usual tool for navigation error description.Considering the feature of pulsed thrust of the impactor,an on-and-off curve was developed for the engine by comparing the zero-effort-miss with the navigation ellipse bound.The results show that this strategy can improve the impacting precision with less fuel consumption.

关 键 词：脉冲比例制导 误差椭圆 开机曲线 小天体撞击 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]