摘要
本文建立了INS和ESGM的误差方程,在此基础上,实现了INS/ESGM组合系统导航过程的卡尔曼滤波器设计。仿真试验表明,本文所设计的滤波器实际可行,利用该滤波器INS/ESGM组合系统能够给出高精度的位置。
Based on the error equations of INS and ESGM,a Kalman filter of INS/ESGM integrated system during navigation task is designed in this paper.By the analyses and simulations,the results show that this navigation filter is usable.Using the filter,INS/ESGM integrated system can provide high accurate data of position ,attitude and velocity.
出处
《中国惯性技术学报》
EI
CSCD
1999年第1期25-29,共5页
Journal of Chinese Inertial Technology
关键词
组合导航系统
静电陀螺监控系统
卡尔曼滤波器
Integrated navigation System
Kalman Filter
Electronstically Supported Gyro Monitor System(ESGM)