Temperature Hysteresis Mechanism and Compensation of Quartz Flexible Accelerometer in Aerial Inertial Navigation System

Strap-down inertial navigation systems (INSs) with quartz flexible accelerometers (QFAs) are widely used in many conditions, particularly in aerial vehicles. Temperature is one of the significant issues impacting the performance of INS. The variation and the gradient of temperature are complex under...

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Bibliographic Details
Published in:Sensors (Basel, Switzerland) Switzerland), 2021-01, Vol.21 (1), p.294
Main Authors: Zhang, Chunxi, Wang, Xin, Song, Lailiang, Ran, Longjun
Format: Article
Language:English
Subjects:
Accelerometers
aerial inertial navigation system
Aircraft
Bias
Calibration
Changing environments
creep effect
Experiments
hysteresis
Hysteresis models
Inertial navigation
Navigation systems
Position errors
Quartz
quartz flexible accelerometer
Regression analysis
Temperature compensation
thermal effect
Viscoelasticity
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Summary:Strap-down inertial navigation systems (INSs) with quartz flexible accelerometers (QFAs) are widely used in many conditions, particularly in aerial vehicles. Temperature is one of the significant issues impacting the performance of INS. The variation and the gradient of temperature are complex under aerial conditions, which severely degrades the navigation performance of INS. Previous work has indicated that parts of navigation errors could be restrained by simple temperature compensation of QFA. However, the temperature hysteresis of the accelerometer is seldom considered in INS. In this paper, the temperature hysteresis mechanism of QFA and the compensation method would be analyzed. Based on the fundamental model, a comprehensive temperature hysteresis model is proposed and the parameters in this model were derived through a temperature cycling test. Furthermore, the comparative experiments in the laboratory were executed to refine the temperature hysteresis model and to verify the effectiveness of the new compensation method. Applying the temperature hysteresis compensation in flight condition, the result shows that the position error (CEP) is restrained from 1.54 nmile/h to 1.29 nmile/h. The proposed temperature hysteresis compensation method improves the performance of INS effectively and feasibly, which could be promoted to other applications of INS in similar temperature changing environment correspondingly.
ISSN:1424-8220
1424-8220
DOI:10.3390/s21010294