Error Analysis of the K-Rb-21Ne Comagnetometer Space-Stable Inertial Navigation System

Cai, Qingzhong; Yang, Ge; Quan, Wei; Song, Ningfang; Tu, Yongqiang; Liu, Yiliang

doi:10.3390/s18020670

Cited by 10 publications

(4 citation statements)

References 32 publications

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“…Considering that the measurement range of an SERFG is relatively small, a navigation scheme based on space-stable platform system is the optimal choice for it. [22] The platform system tracks an inertial coordinate system, so the angular rate input felt by the SERFG is constant. Therefore, from the perspective of future applications of an SERFG, the method is still feasible.…”

Section: Resultsmentioning

confidence: 99%

Low drift nuclear spin gyroscope with probe light intensity error suppression*

et al. 2019

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A nuclear spin gyroscope based on an alkali-metal–noble-gas co-magnetometer operated in spin-exchange relaxation-free (SERF) regime is a promising atomic rotation sensor for its ultra-high fundamental sensitivity. However, the fluctuation of probe light intensity is one of the main technical error sources that limits the bias stability of the gyroscope. Here we propose a novel method to suppress the bias error induced by probe light intensity fluctuations. This method is based on the inherent magnetic field response characteristics of the gyroscope. By the application of a bias magnetic field, the gyroscope can be tuned to a working point where the output signal is insensitive to probe light intensity variation, referred to herein as ‘zero point’, thus the bias error induced by intensity fluctuations can be completely suppressed. The superiority of the method was verified on a K–Rb–21Ne co-magnetometer, and a bias stability of approximately 0.01 °/h was obtained. In addition, the method proposed here can remove the requirement of the closed-loop control of probe light intensity, thereby facilitating miniaturization of the gyroscope volume and improvement of reliability.

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Section: Resultsmentioning

confidence: 99%

Low drift nuclear spin gyroscope with probe light intensity error suppression*

et al. 2019

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“…Pendulous integrating gyroscopic accelerometers (PIGA), which provide acceleration information named as a specific force for vehicles [ 1 , 2 ], is one type of core inertial sensor used in inertial navigation systems (INS). Although other types of accelerometer for INS, including quartz flexible accelerometers (QFA) [ 3 , 4 ], microelectromechanical systems (MEMS) capacitive accelerometers [ 5 , 6 ] and resonant accelerometers [ 7 , 8 ] have the advantages of simple structures and low cost compared with PIGA, PIGA is still an irreplaceable inertial sensor for supporting INS in applications with ultra-high navigation and guidance accuracy requirements such as intercontinental ballistic missiles (ICBM) and ocean-going submarines [ 9 ].…”

Section: Introductionmentioning

confidence: 99%

Precise Measurement and Compensation of the Micro Product of Inertia for Float Assembly in Pendulous Integrating Gyroscopic Accelerometers

Zhou

Yang

Niu

et al. 2023

Sensors

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Nonlinear error has become the most critical factor restricting the measurement accuracy of pendulous integrating gyroscopic accelerometers (PIGA) during their improvement. The key to nonlinear error suppression for PIGA is the precise measurement and compensation of the micro product of inertia (MPOI) of the float assembly. However, the existing equipment and procedure for product of inertia (POI) measurement and compensation do not meet the accuracy requirements for MPOI. To solve this problem, novel equipment and procedures are proposed for the measurement and compensation of MPOI. The principle of the proposed measurement method is to simulate the error produced by MPOI in PIGA by using a single-axis turntable to rotate the float assembly along the eccentric axis to generate a centrifugal moment due to MPOI. The principle of the proposed compensation method is to remove the asymmetric mass to reduce the MPOI to zero. Through experimental validation, it is concluded that: (1) the measurement and compensation accuracy of the proposed method are better than 1 × 10−10 kg·m2 and 3 × 10−10 kg·m2, respectively; (2) the proposed method is validated as the MPOI is reduced from 7.3 × 10−9 kg·m2 to 3 × 10−10 kg·m2 for a real float assembly in PIGA, and the quadratic error of PIGA is reduced from 10−5/g0 to 3 × 10−7/g0.

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“…Its advantages include global coverage, high positioning accuracy, and real-time performance [10][11][12]. However, GNSS signals may be attenuated in environments with dense obstructions such as urban areas, tunnels, or forests, leading to inaccurate train positioning [13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Estimation and Compensation of Heading Misalignment Angle for Train SINS/GNSS Integrated Navigation System Based on Observability Analysis

Chen,

Yang,

2023

Applied Sciences

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The inertial Navigation Systems/global navigation satellite system (SINS/GNSS) has become a research hotspot in the field of train positioning. However, during a uniform straight-line motion period, the heading misalignment angle of the SINS/GNSS is unobservable, resulting in the divergence of the heading misalignment angle and ultimately causing a divergence in the train’s speed and position estimation. To address this issue, this paper proposes an estimation and compensation method for the heading misalignment angle for train SINS/GNSS integrated navigation system based on an observability analysis. When the train enters a straight-line segment, the alignment of the train’s sideslip angle and the satellite velocity heading angle allows the achievement of velocity heading observation values that resolve the issue. In a curved segment, the heading angle becomes observable, allowing for an accurate estimation of the SINS’s heading misalignment angle using GNSS observations. The results showed that, whether the train is on a straight or curved track, the position estimation accuracy meets the simulation design criteria of 0.1 m, and the heading accuracy is better than 0.25°. In comparison to the results of pure GNSS position and velocity-assisted navigation, where heading divergence occurs during constant velocity straight-line segments, the method proposed in this paper not only converges but also achieves an accuracy comparable to the GNSS velocity-based heading alignment. The simulation results demonstrate that the proposed strategy significantly improves the accuracy of the heading misalignment angle estimation, thereby enhancing the accuracy of speed and position estimation under a GNSS-denied environment.

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Error Analysis of the K-Rb-21Ne Comagnetometer Space-Stable Inertial Navigation System

Cited by 10 publications

References 32 publications

Low drift nuclear spin gyroscope with probe light intensity error suppression*

Low drift nuclear spin gyroscope with probe light intensity error suppression*

Precise Measurement and Compensation of the Micro Product of Inertia for Float Assembly in Pendulous Integrating Gyroscopic Accelerometers

Estimation and Compensation of Heading Misalignment Angle for Train SINS/GNSS Integrated Navigation System Based on Observability Analysis

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