Observability analysis of in-flight calibration of gyros and attitude sensors on orbit

Heo, Sejong; Kim, Hyun‐Jin; Park, Chan Gook

doi:10.1109/plans.2016.7479795

Cited by 5 publications

(4 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The EKF method in [8], the MHE method in [29] and the proposed method are evaluated via numerical simulation. All the methods are initialized with an attitude of [1, 1, 1] T deg and a gyroscope bias of [0, 0, 0] T deg/s.…”

Section: A Simulation Experimentsmentioning

confidence: 99%

“…In the structure of EKF, nonlinear attitude equations are used in the forward estimation process and the estimated attitude is updated in a recursive manner using the measurement data. Common implementations of EKF are the multiplicative extended Kalman filter (MEKF) [5]- [8] and the additive extended Kalman filter (AEKF) [9]. Although the extended Kalman filter is a popular method for attitude estimation, it may fail when the state or measurement models are highly nonlinear or a satisfactory a priori estimate of the state is unavailable.…”

mentioning

confidence: 99%

See 1 more Smart Citation

A Factor Graph Approach for Attitude Estimation of Spacecraft Using a Stellar Gyroscope

et al. 2019

View full text Add to dashboard Cite

A stellar gyroscope is an attitude sensor that is composed of a micro star sensor and a microelectro-mechanical system gyroscope. The attitude is the output by fusing the information of the two sensors. Due to the processing of the star image from the star sensor, a measurement delay is introduced and can affect the performance of the fusion of the two sensors. In this paper, a factor graph method that is based on a sliding window is investigated for dealing with the measurement delay. Temporary factors are calculated to temporarily occupy the places of the factors that are under processing, and sliding window incremental smoothing is only performed with a set of factors and states after the delayed measurement has arrived. To reduce the frequency of attitude calculation based on a star image, the keyframe strategy is adopted. Only in keyframes, the attitude is solved by using the star image and used as the measurement of the factor. In nonkeyframes, only the star positions in the star images are determined, with a robust star tracking method that is aided by the gyroscope. Moreover, a high-rate low-latency output framework that is by a gyroscope is proposed for accelerating the attitude output rate. According to the results of the experiments on simulated data, the proposed method can overcome the problem of measurement delay and is more effective than the compared methods. According to the results of the experiments on real data, the proposed method can be used in applications. INDEX TERMS Attitude estimation, factor graph, temporary factor, sliding window incremental smoothing. I. INTRODUCTION With an ever-widening range of space missions becoming feasible, attitude determination performance is critical for many spacecraft. Since a small spacecraft may have a limited payload, only compact, low-power and miniature sensors can be used on satellites. Using new sensor technologies, such as micro-electro mechanical system(MEMS) gyroscopes and active pixel sensor (APS) imaging devices, suitable attitude sensors, namely, stellar gyroscope, has been developed by many institutes, such as the Charles Stark Draper Laboratory, University of Kentucky and StarVision Technologies [1]-[3]. A stellar gyroscope is composed of a MEMS gyroscope and a micro star sensor and is small, lightweight and inexpensive [4]. Under typical operating conditions, a star sensor can output attitude information accurately with a low output rate. The output rate of the gyroscope is high; however, the angular velocity suffers due to long-term stability, namely, The associate editor coordinating the review of this manuscript and approving it for publication was Zheng Hong Zhu.

show abstract

Section: A Simulation Experimentsmentioning

confidence: 99%

mentioning

confidence: 99%

A Factor Graph Approach for Attitude Estimation of Spacecraft Using a Stellar Gyroscope

et al. 2019

View full text Add to dashboard Cite

show abstract

“…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%

“…took the star sensor installation error, gyro bias, and accelerometer bias as state variables, and they could be estimated by the optimal estimation method. In Ref 17,. the attitude and gyro errors can be calibrated by attitude excitation, and the observability is analyzed.…”

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:

View full text Add to dashboard Cite

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.

show abstract

Analysis on Observability and Performance of INS-Range Integrated Navigation System Under Urban Flight Environment

Lee

Kim

Lee

et al. 2020

J. Electr. Eng. Technol.

View full text Add to dashboard Cite

Observability analysis of in-flight calibration of gyros and attitude sensors on orbit

Cited by 5 publications

References 8 publications

A Factor Graph Approach for Attitude Estimation of Spacecraft Using a Stellar Gyroscope

A Factor Graph Approach for Attitude Estimation of Spacecraft Using a Stellar Gyroscope

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

Analysis on Observability and Performance of INS-Range Integrated Navigation System Under Urban Flight Environment

Contact Info

Product

Resources

About