An On-Orbit Calibration Method of Star Sensor Based on Angular Distance Subtraction

Wu, Liang; Xu, Qian; Chen, Han; Zhang, Kaixuan

doi:10.1109/jphot.2021.3075684

Cited by 5 publications

(2 citation statements)

References 14 publications

(15 reference statements)

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“…Following the launch of the star sensor, the parameters of the star sensor will alter owing to the vibration, impact, and changes in the working environment during the launch process [14,15]. The internal parameters of the star sensor will be recalibrated through the autonomous calibration technology, after the launch, to ensure its accuracy and reliability [16,17].…”

Section: Introductionmentioning

confidence: 99%

Error suppression method of SINS/CNS integrated navigation based on diametrical stargazing

Xu,

Zhou,

Pang

et al. 2023

Meas. Sci. Technol.

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The strap-down inertial navigation system (SINS)/celestial navigation system (CNS) integrated navigation system is widely used in the aerospace field owing to its unique advantages. The internal parameter errors of the star sensor are one of the main factors that affect the navigation accuracy. In this paper, an error suppression method based on diametrical stargazing has been designed to suppress the navigation errors caused by the internal parameter errors of the star sensor. First, a SINS/CNS integrated navigation model based on Kalman filter has been established. Then the influence of the principal point error, image-plane tilt error and distortions of the optical system on the measurement accuracy of the star sensor has been analyzed, and the process of introducing the errors into the measurement equation is obtained. Finally, for different errors, two stargazing methods are designed to suppress the impact of these errors on navigation accuracy and meanwhile, the constant errors of the inertial device can be modulated. The simulation results demonstrate that the proposed method can effectively improve the positioning accuracy of the system, and verify the effectiveness of the algorithm.

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Section: Introductionmentioning

confidence: 99%

Error suppression method of SINS/CNS integrated navigation based on diametrical stargazing

Xu,

Zhou,

Pang

et al. 2023

Meas. Sci. Technol.

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“…The iteration calibration method, which considers the weight of different stars, is proposed in [ 18 ]. In addition, an angular distance subtraction on-orbit calibration method is presented in [ 19 ].…”

Section: Introductionmentioning

confidence: 99%

Attitude Correlated Frames Based Calibration Method for Star Sensors

Ma,

Xiao,

Tang

et al. 2023

Sensors

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Star sensors undergo laboratory calibration before they leave the factory. In addition, recalibration is necessary after they experience vibration, deformation, etc. Using the analysis of attitude-dependent and attitude-independent interstar angular invariance calibration methods (IAICMs) as a reference, an attitude-correlated frame-based calibration method (ACFCM) is proposed in this work, which combines the advantages of both methods. Using outdoor star observations, the ACFCM correlates star image frames obtained at different times via a strapdown gyro unit. As a result, the number of efficient star images for calibration increases rapidly and the distribution of star images becomes much more uniform, thus improving the calibration accuracy of the star sensor. A simulation and experimental tests were designed and carried out. Both the simulation and experimental results verify the feasibility of the proposed ACFCM method. Furthermore, by comparing our method with the IAICMs, the repeatability and reliability of the principal point obtained from the calibration with the ACFCM method proposed in this work were significantly improved.

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On-orbit high-precision calibration for deep-coupled parameters of star sensor and gyroscope systems

Yi,

Ma,

Long

et al. 2024

Opt. Express

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To enhance the dynamic performance and stability of spacecraft attitude measurement, a commonly adopted approach is to integrate a star sensor with an inertial gyroscope. While an integrated sensor system offers benefits in high-precision and high-dynamic scenarios, it also introduces errors in the extrinsic parameters of the camera and gyroscope, directly contributing to increased fixed error in attitude determination. Hence, real-time correction of integrated system parameters becomes crucial for enhancing the accuracy of attitude estimation. However, a deep coupling relationship exists between the camera's principal point and the extrinsic parameters of the two sensors, unified calibration of system parameters increases the computational time to decouple all the parameters. In response to this challenge, a stepwise calibration method for system parameters is proposed. Firstly, the calibration of camera intrinsic parameters leverages the principle of invariant interior star angles, which are independent of extrinsic parameters. Secondly, based on the observation vector error model of the integrated sensor, observation equations and state equations are constructed, followed by proposing a 4-position maneuver strategy based on observability analysis to achieve rapid decoupling of gyroscope bias, attitude error, and extrinsic parameters. Simulation results affirm the effectiveness of the proposed method, extrinsic parameter errors reaching the arc-second level.

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An On-Orbit Calibration Method of Star Sensor Based on Angular Distance Subtraction

Cited by 5 publications

References 14 publications

Error suppression method of SINS/CNS integrated navigation based on diametrical stargazing

Error suppression method of SINS/CNS integrated navigation based on diametrical stargazing

Attitude Correlated Frames Based Calibration Method for Star Sensors

On-orbit high-precision calibration for deep-coupled parameters of star sensor and gyroscope systems

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