Abstract
The precision of star sensor is usually influenced by the carrier dynamic. In this work, a hybrid strap-down inertial/celestial integrated navigation system is raised. The inertial measurement unit is integrated installation with the star sensor, which ensures the attitude variation of the star sensor could be indiscriminately acquired. Then the star images are shifted and rotated according to the inertial information. Consequently, the star image stabilization is achieved. The experiment results demonstrates that the standard variance of the star centroid coordinates after stabilization is about 0.1 pixel for both uniform angular motion and sine angular motion when the average velocity is less than 3 °/S. The approach provided can significantly enhance the dynamic adaptation and effectively improve the detection capacity for the star sensor. It shows compact structure, small volume, light weight and offers a possible solution for the contradiction between high precision and miniaturization in airborne star sensor, which has positive guiding significance for engineering application of airborne integrated navigation system.
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Acknowledgement
The authors are grateful to the anonymous reviewers for their critical and constructive review of the manuscript. This study was co-supported by the Key Basic Research Projects of The Foundation Strengthening Plan (No. 2020-JCJQ-ZD-136).
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Pu, C., Xiaodong, H., Xiaokun, D., Ke, L., Qing, W. (2022). An Inertial Information Based Image Stabilization Method for Airborne Hybrid Strap-Down Inertial/Celestial Integrated Navigation System. In: Proceedings of the 5th China Aeronautical Science and Technology Conference. Lecture Notes in Electrical Engineering, vol 821. Springer, Singapore. https://doi.org/10.1007/978-981-16-7423-5_96
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DOI: https://doi.org/10.1007/978-981-16-7423-5_96
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