A dynamic error excitation and calibration method for high precision IMU

被引：0
|
作者：
Xing, Li [1 ,2 ]
Bai, Qingqing [3 ]
Xiong, Zhi [1 ,2 ]
Luo, Wei [1 ,2 ]
Liu, Jianye [1 ,2 ]
机构：
[1] Nanjing Univ Aeronaut & Astronaut, Nav Res Ctr, Nanjing 211100, Jiangsu, Peoples R China
[2] Satellite Commun & Nav Collaborat Innovat Ctr, Nanjing 211100, Jiangsu, Peoples R China
[3] Shanghai Aircraft Customer Serv Co Ltd, Shanghai 200240, Peoples R China
来源：
2016 IEEE CHINESE GUIDANCE, NAVIGATION AND CONTROL CONFERENCE (CGNCC) | 2016年
基金：
中国国家自然科学基金;
关键词：
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
According to the urgent need of high-precision navigation system to future fighters, this paper researches on a dynamic error excitation and calibration method for high-precision IMU. The Kalman filter model including installation errors, scale factor errors and random constant errors of the inertial measurement unit (IMU) as state variables for online identification is established. The relationship between IMU errors and aircraft maneuver manner is derived, and the dynamic flight track to incite IMU errors is designed. Simulation results verify the feasibility of the proposed dynamic error parameter excitation and calibration method, which can incite and identify the IMU error effectively. With the error identification results, the IMU errors are compensated and the precision of the INS is improved significantly.
引用
收藏
页码：1571 / 1575
页数：5
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