摘要
针对无阻尼惯导系统的误差特点,设计了适合航空应用的惯性(INS)/天文(CNS)/Doppler组合导航系统,建立了该组合导航系统卡尔曼滤波模型。仿真试验表明,该组合导航系统能为飞行体提供精确的导航信息。
According to the characteristics of error model of INS without damping, an integrated INS/CNS/Doppler navigation system for aeronautic field is designed, and the Kalman filtering model for the system is built up. Digital simulation shows that the integrated navigation system can provide high accurate navigating information for aeronautic vehicle.
出处
《中国惯性技术学报》
EI
CSCD
2004年第2期31-35,共5页
Journal of Chinese Inertial Technology
基金
国防基础研究项目
