摘要
对弹道导弹的主动段跟踪是导弹防御中重要的环节。针对此问题提出了一种基于推力加速度模板的主动段跟踪算法,该算法需要主动段推力加速度信息支持。给出了一种简捷的推力加速度模板构建方法。利用近常速运动模型描述了导弹运动特性,解决了对导弹发射时间的估计问题和模板概率的递推计算问题,并将该方法应用到空间预警系统中,通过仿真验证了该方法具有较好的识别效果,位置和速度估计误差都接近于CRLB限。
The tracking of ballistic missile under boost-phase is more important in the missile defense program. This paper presents a new trajectory tracking algorithm based on the thrust acceleration profile which depends on the knowledge of the thrust acceleration and missile type, and then a concise method of profile is presented. In this paper the missile movement is described by the nearly constant velocity model, and the estimation problem of the launch time and the calculation of profile probabilities are resolved. This approach applied in the space-based early warning system, via the simulation, the result shows that this algorithm has the higher matching probability, and the estimated errors are closed to the CRLB.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2006年第3期385-389,共5页
Journal of Astronautics
关键词
导弹防御
弹道跟踪
KALMAN滤波
Ballistic missile defense
Trajectory tracking
Kalman filter
