Accelerometer Bias and Star Sensor Installation Error Joint Calibration for the SINS/CNS Integrated Navigation System Using Attitude Maneuver

被引：1

作者：

Ning, Xiaolin ^{[1
]}

Yang, Yuqing ^{[2
]}

Liang, Xiaoyu ^{[2
]}

Zhang, Jie ^{[2
]}

机构：

[1] Beihang Univ BUAA, Res Inst Frontier Sci, Beijing 100191, Peoples R China

[2] Beihang Univ BUAA, Sch Instrumentat Sci & Optoelect Engn, Beijing 100191, Peoples R China

来源：

GUIDANCE NAVIGATION AND CONTROL | 2022年 / 02卷 / 02期

关键词：

SINS/CNS integrated navigation; accelerometer bias; star sensor installation error; calibration method; OBSERVABILITY ANALYSIS; INERTIAL NAVIGATION;

D O I：

10.1142/S2737480722500066

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

The integrated strap-down inertial navigation system/celestial navigation system (SINS/CNS) is an important autonomous navigation method with effective concealment and high precision. Both accelerometer bias and star sensor installation error are important factors that affect the performance of this navigation system, which need to be calibrated and compensated. A new accelerometer bias and star sensor installation error joint calibration method for the SINS/CNS integrated navigation system is proposed. In this newly proposed method, the installation error of star sensor is augmented to the state vector, and the star vector, nadir angle, horizontal position error and velocity error are used as measurements to calibrate the two errors mentioned above. Simulations show that both accelerometer bias and star sensor installation error can be calibrated effectively.

引用

页数：15