中国民航大学学报 ›› 2020, Vol. 38 ›› Issue (2): 24-27.

• 民用航空 • 上一篇    下一篇

IMU 的加速度计误差参数辨识方法研究

王力,习先强   

  1. (中国民航大学电子信息与自动化学院,天津300300)
  • 收稿日期:2019-03-09 修回日期:2019-04-28 出版日期:2020-04-25 发布日期:2020-05-13
  • 作者简介:王力(1973—),男,重庆人,教授,博士,研究方向为导航与飞行控制、机载电子故障诊断.

Identification method of accelerometer error parameter based on IMU

WANG Li, XI Xianqiang   

  1. (College of Electronic Information and Automation, CAUC, Tianjin 300300, China)
  • Received:2019-03-09 Revised:2019-04-28 Online:2020-04-25 Published:2020-05-13

摘要: 为了提高惯性测量单位(IMU)加速度计的输出性能,提出了24 位置法辨识加速度计误差参数。首先根据加速度计的输入输出方程建立加速度计的输出误差模型,然后利用24 位置法对加速度计的误差模型参数进行辨识,详细设计了24 位置法的标定过程,给出了加速度计的标度因数、不对准角、零偏的计算方式,最后利用转台进行位置试验来采集数据并计算分析。实验结果表明,该方法能够快速地辨识出加速度计的误差参数,建立的加速度计误差模型准确。

关键词: 加速度计, 位置试验, 误差标定, 不对准角

Abstract: As the core component of IMU, the accelerometer accuracy directly affects the IMU accuracy. In order to improve the output performance of accelerometer, a 24-position method is proposed to identify the accelerometer error parameters. Firstly, the accelerometer output error model is established according to the input and output formula of accelerometer. Then the accelerometer error model parameters are identified by 24-position method and the calibration process of which is designed in details giving the calculation method of scale factor, misalignment angle and zero offset of the accelerometer. Finally, position test is performed by turntable to collect data and to conduct calculation as well as data analyses. Experimental results show that the proposed method can quickly identify the accelerometer error parameters and establish an accurate accelerometer error model.

Key words: accelerometer, position test, error calibration, misalignment angle

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