摘要
研究了FOG SINS/GPS组合导航系统不同步时间产生的原因及其鉴定方法。在该鉴定方法中,通过考察FOG SINS/GPS组合导航系统不同步时间与纵向加计零偏的卡尔曼滤波稳态估计值之间的定量关系,给出一个经验公式。使用某型光纤陀螺捷联惯导系统采集的静态导航数据和模拟的飞行动态轨迹进行了半物理仿真,仿真结果表明,当不同步时间小于0.5s时,该鉴定方法的估计精度优于80 ms。
Causes and evaluation methods of time synchronization error of FOG SINS/GPS integrated navigation system were stud- ied. In the evaluation method, by examining the quantitative relationship between time synchronization error of integrated naviga- tion system and steady-state estimation of longitudinal accelerometer bias by Kalman filter, an empirical formula was given. A semi-physical simulation was conducted with stable navigation data from a FOG SINS and simulated flight track. The simulation re- sults indicate that the precision of proposed method is better than 80ms when the time synchronization error is 0. 5s.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第3期37-40,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
