Abstract
The paper studies the aircraft astro-inertial navigation system, which consists of an astronomical navigation system installed on a gyro-stabilized platform of inertial navigation system. The errors of this system arising from various disturbing factors are investigated. Methods based on system correction channels formation and using adaptive estimation algorithm are proposed for reducing these errors. A simulation using semi-natural experiment data was carried out for determining the accuracy of error compensation. The results demonstrate the accuracy and effectiveness of the proposed methods in correcting astro-inertial navigation systems.
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