混合式惯导系统姿态四元数连续自标定模型

doi:10.13700/j.bh.1001-5965.2018.0691

北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (7): 1424-1434.doi: 10.13700/j.bh.1001-5965.2018.0691

混合式惯导系统姿态四元数连续自标定模型

王琪, 汪立新, 周小刚, 沈强

火箭军工程大学导弹工程学院, 西安 710025

收稿日期:2018-11-23 出版日期:2019-07-20 发布日期:2019-07-25
通讯作者: 汪立新 E-mail:17765861219@163.com
作者简介:王琪男,博士研究生。主要研究方向:惯性系统及仪器;汪立新男,博士,教授,博士生导师。主要研究方向:惯性系统及测试;周小刚男,博士,讲师。主要研究方向:惯性系统及测试;沈强男,博士研究生。主要研究方向:数据处理和信息融合。
基金资助:
国家自然科学基金（61503392）；陕西省自然科学基金（2015JQ6213）；航空科学基金（201501U8001）

Attitude quaternion continuous self-calibration model of hybrid inertial navigation system

WANG Qi, WANG Lixin, ZHOU Xiaogang, SHEN Qiang

College of Missile Engineering, Rocket Force University of Engineering, Xi'an 710025, China

Received:2018-11-23 Online:2019-07-20 Published:2019-07-25
Supported by:
National Natural Science Foundation of China (61503392); Natural Science Foundation of Shaanxi Province (2015 JQ6213); Aeronautical Science Foundation of China (201501U8001)

摘要/Abstract

摘要： 混合式惯导系统作为一种新型惯导系统，具有三轴全姿态物理平台、捷联姿态算法和系统装机自标定等特点。针对以上特点，为提高其导航定位精度，在混合式惯导系统框架角约束方程的基础上，利用姿态四元数代替欧拉角描述混合式惯导系统中三轴物理平台的转动，建立了一种混合式惯导系统姿态四元数连续自标定模型对其进行误差系数标定。针对该模型的特点，对传统的无迹卡尔曼滤波（UKF）算法进行改进，提出了一种基于奇异值分解的四元数无迹卡尔曼滤波（SVD-QUKF）算法进行模型误差系数辨识。仿真和试验结果表明，基于SVD-QUKF算法，四元数连续自标定模型能够以低于1%的相对误差标定出混合式惯导系统所有的误差系数，在标定精度和计算速度上相比基于传统UKF算法的框架角自标定模型都具有一定优势。

关键词: 混合式惯导系统, 连续自标定, 姿态四元数, 无迹卡尔曼滤波(UKF), 奇异值分解(SVD)

Abstract: As a kind of new inertial navigation system, the hybrid inertial navigation system has the characteristics of three-axis physical platform, strapdown attitude algorithm and installed self-calibration. Based on these characteristics and in order to improve the accuracy of hybrid inertial navigation system the attitude quaternion is used to replace the traditional Euler angle to represent the rotation of three-axis physical platform in the continuous self-calibration, and the attitude quaternion continuous self-calibration model of hybrid inertial navigation system based on the gimbal angle equation is established for its error coefficient estimation.Then a quaternion unscented Kalman filter based on singular value decomposition (SVD-QUKF) is proposed by improving the traditional unscented Kalman filter (UKF) based on the characteristics of the attitude quaternion model. The simulation and experimental results prove that the proposed attitude quaternion continuous self-calibration model based on the SVD-QUKF can calibrate all the error coefficients of hybrid inertial navigation system with the relative error less than 1%, and the calibration precision and the computing speed are better than the traditional gimbal angle model based on UKF.

Key words: hybrid inertial navigation system, continuous self-calibration, attitude quaternion, unscented Kalman filter (UKF), singular value decomposition (SVD)

中图分类号:

U666.1

王琪, 汪立新, 周小刚, 沈强. 混合式惯导系统姿态四元数连续自标定模型[J]. 北京航空航天大学学报, 2019, 45(7): 1424-1434.

WANG Qi, WANG Lixin, ZHOU Xiaogang, SHEN Qiang. Attitude quaternion continuous self-calibration model of hybrid inertial navigation system[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2019, 45(7): 1424-1434.

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混合式惯导系统姿态四元数连续自标定模型

Attitude quaternion continuous self-calibration model of hybrid inertial navigation system

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