摘要
战略导弹中段机动是目前正在研究的一种较为有效的突防技术。为实现对大气层外杀伤拦截弹(EKV,exoatmospheric kill vehicle)的针对性、有效的机动规避,必须预先解决实时、精确获取EKV状态信息的问题。为此,设计了一种基于弹道导弹惯性导航信息的单颗红外探测卫星定位、测速方案,建立了针对EKV的单星探测定位测速模型,并基于该模型建立了仿真系统。在此基础上,在给定的不同卫星定位误差条件下对本方案的定位测速误差进行了仿真计算与分析,结果表明该方案可以实现定位、测速,具备理论可行性。
The maneuvering penetration in the middle-course flight of the strategic guided missile is a kind of effective penetration technology. In order to evade the interception of EKV effectively, the problem of how to obtain the real-time precise appearance information of EKV should be solved in advance. Based on inertial nav- igation information of ballistic missiles, a technology of measurement with single infrared satellite is presented and researched. Models to measure the position and speed of EKV are given and the simulated system is built. Finally, according to different location error conditions, the speed error is simulated and analyzed. The simulation results show that this scheme could measure the position and speed of EKV and is feasible theoretically.
出处
《测控技术》
CSCD
北大核心
2010年第2期39-43,共5页
Measurement & Control Technology
关键词
单星探测
导航信息
定位测速
EKV
detecting with single satellite
navigation information
measure the location and speed
EKV
