摘要
针对弹道导弹的特点,在分析陆基单站定位原理的基础上,详细建立了单站定位的误差模型,并设计了两种可行的SINS/陆基单站组合导航系统方案:松组合导航系统和紧组合导航系统。通过仿真对比,紧组合导航系统收敛性好、导航精度高,能够很好地抑制惯导系统误差积累现象,有较高的导航性能。
According to the characteristics of ballistic missile,based on the analysis of land-based single station positioning system,the error model of single station location system is established in detail,and two kinds of SINS / land-based single station schemes with regard to integrated navigation system are designed,which are loosely integrated navigation system and tightly integrated navigation system. The simulation results show that the tightly integrated navigation system has good convergence and navigation precision,and can restrain the error accumulation of inertial navigation system with better navigation performance.
作者
王勋
王新龙
车欢
张金鹏
Wang Xun Wang Xinlong Che Huan Zhang Jinpeng(School of Astronautics, Beihang University, Beijing 100191, China Space Star Technology Co., Ltd, Beijing 100086, China China Airborne Missile Academy, Luoyang 471009, China)
出处
《航空兵器》
2016年第6期55-60,共6页
Aero Weaponry
基金
航空科学基金项目(20130151004
2015ZC51038)
卫星应用研究院创新基金项目(2014_CXJJ-DH_01)
关键词
陆基单站
捷联惯导
弹道导弹
组合导航
land-based single station
SINS
ballistic missile
integrated navigation
