In-Flight Calibration of Gyros and Star Sensor With Observability Analysis for SINS/CNS Integration

Yang, Yanqiang; Zhang, Chunxi; Lu, Jiazhen; Zhang, Hao

doi:10.1109/jsen.2017.2754464

Cited by 23 publications

(11 citation statements)

References 16 publications

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“…Some literatures show that the accuracy of error coefficient calibration is related to the system observability. 17,20 Better observability will significantly improve the calibration accuracies of error coefficients. At present, there are four main methods to analyze the system observability: the piece-wise constant system (PWCS), 21 the singular value decomposition (SVD) 22 to analyze the observability matrix, the fisher information matrix (FIM), [23][24][25] and the Lie algebra.…”

Section: Introductionmentioning

confidence: 99%

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An optimal calibration method for gyro and star sensor based on observability analysis

Zhao

Wang

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The major challenge of current strapdown inertial navigation system/celestial navigation system (SINS/RCNS) is failing to calibrate all the error coefficients of gyro and star sensor in-flight accurately, which will lead to the attitude accuracy degradation. To address this question, this paper proposes an optimal calibration method based on observability analysis. Here, we derive the star sensor measurement model with respect to initial alignment errors, gyro errors, and star sensor installation errors. And the observability analysis is employed to explain the reason why all the error coefficients can be estimated effectively by three maneuvers merely. Finally, the optimal observation sequence is determined based on the fisher information matrix (FIM). The proposed optimal calibration method is evaluated by a representative suborbital flight vehicle trajectory, which represents significant improvements in estimation accuracy of error coefficients, and realizes the attitude accuracy enhancements.

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Section: Introductionmentioning

confidence: 99%

“…26,27 For the first two methods, it is difficult to analyze the observability of a single error coefficient. 20 For the latter method, if the dimension of the dynamical system is high, it will significantly increase the computational complexity. 28 Therefore, the FIM is exploited to determine the optimal observation sequence in this paper.…”

Section: Introductionmentioning

confidence: 99%

An optimal calibration method for gyro and star sensor based on observability analysis

Zhao

Wang

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…However, the GNSS relies on signals from artificial satellites, and therefore lacks autonomy and is susceptible to artificial interference [ 9 ]. The celestial navigation system (CNS) is an autonomous navigation system that has lower positioning accuracy than the GNSS but has the advantage of not accumulating navigation error and a strong ability to resist electromagnetic interference [ 10 , 11 , 12 ]. Thus, researchers have also investigated the INS/CNS integrated navigation system, which incorporates the measurement information from the CNS to correct the deviations in the INS.…”

Section: Introductionmentioning

confidence: 99%

A Robust INS/SRS/CNS Integrated Navigation System with the Chi-Square Test-Based Robust Kalman Filter

Gao

Hong

et al. 2020

Sensors

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In order to achieve a highly autonomous and reliable navigation system for aerial vehicles that involves the spectral redshift navigation system (SRS), the inertial navigation (INS)/spectral redshift navigation (SRS)/celestial navigation (CNS) integrated system is designed and the spectral-redshift-based velocity measurement equation in the INS/SRS/CNS system is derived. Furthermore, a new chi-square test-based robust Kalman filter (CSTRKF) is also proposed in order to improve the robustness of the INS/SRS/CNS navigation system. In the CSTRKF, the chi-square test (CST) not only detects measurements with outliers and in non-Gaussian distributions, but also estimates the statistical characteristics of measurement noise. Finally, the results of our simulations indicate that the INS/SRS/CNS integrated navigation system with the CSTRKF possesses strong robustness and high reliability.

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“…When the installation parameters of the star sensor in the satellite body coordinate system are measured exactly, the virtual body coordinate systems determined by the installation parameters of the different star sensor combination modes are consistent, and the orientation of the satellite body in the J2000 celestial coordinate system can be calculated correctly. However, owing to vibrations and thermal shocks that arise during launch and orbit penetration process, there is a gap between the on-orbit actual installation parameters and the on-ground measured parameters [10]. Therefore, the virtual body coordinate systems determined by the different star sensor combination modes are inconsistent, causing systematic errors in the precise attitude determinations of different combination modes [11].…”

Section: Introductionmentioning

confidence: 99%

On-Orbit Calibration of Installation Parameter of Multiple Star Sensors System for Optical Remote Sensing Satellite with Ground Control Points

Wang

Zhu

2020

Remote Sensing

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Owing to the vibrations and thermal shocks that arise during the launch and orbit penetration process, the on-orbit installation parameters of multiple star sensors are different from the on-ground measured parameters, causing inconsistencies in the attitude determinations from different combination modes and seriously affecting the geometric accuracy of high-resolution optical remote sensing images. This study presents an on-orbit calibration approach for the installation parameters of a multiple star sensors system using ground control points (GCPs). Based on the on-ground installation parameters of the optical axes of conventional star sensors, a fiducial coordinate system is proposed as the calibration coordinate system. The installation parameters of the conventional star sensors are calibrated using the statistical characteristics of angles between axes of the star sensor and three fiducial vectors in the J2000 celestial coordinate system. Based on the GCPs, the relative fiducial parameters are calculated, and the installation parameter of unconventional star sensor is then calibrated with the relative fiducial parameters and statistical characteristics of angles. It can be used for high-resolution optical remote sensing satellite measuring with only two star sensors to unify the fiducial coordinate system. The proposed method is tested using simulated data and on-orbit measurement data. The results demonstrate that the proposed method can calibrate the optical axis of the star sensor without the restriction of the accuracy of horizontal axis. Moreover, the star sensor with a large installation angle error can be calibrated well using the proposed approach. The results of attitude determinations from different star sensor combination modes are consistent, and the geometric accuracy of the remote sensing images is significantly improved.

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In-Flight Calibration of Gyros and Star Sensor With Observability Analysis for SINS/CNS Integration

Cited by 23 publications

References 16 publications

An optimal calibration method for gyro and star sensor based on observability analysis

An optimal calibration method for gyro and star sensor based on observability analysis

A Robust INS/SRS/CNS Integrated Navigation System with the Chi-Square Test-Based Robust Kalman Filter

On-Orbit Calibration of Installation Parameter of Multiple Star Sensors System for Optical Remote Sensing Satellite with Ground Control Points

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