Accelerometer Bias and Star Sensor Installation Error Joint Calibration for the SINS/CNS Integrated Navigation System Using Attitude Maneuver-Reference-Cited by-同舟云学术

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

Published:2022-05-05 Issue:02 Volume:02 Page:
ISSN:2737-4807
Container-title:Guidance, Navigation and Control
language:en
Short-container-title:Guid. Navigat. Control

Author:

Ning Xiaolin¹,Yang Yuqing²,Liang Xiaoyu²,Zhang Jie²

Affiliation:

1. Research Institute for Frontier Science, Beihang University (BUAA), Beijing 100191, P. R. China

2. School of Instrumentation Science & Opto-electronics Engineering, Beihang University (BUAA), Beijing 100191, P. R. China

Abstract

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.

Publisher

World Scientific Pub Co Pte Ltd

Subject

General Medicine

Link

https://www.worldscientific.com/doi/pdf/10.1142/S2737480722500066

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