Abstract
In this paper, to solve the correction problem of star vector error induced by the aero-optic effect under hypersonic conditions, and to improve the navigation accuracy further, a novel method of star centroid error correction is proposed. The method is based on the star triangle internal angles, which can effectively use the prior information to estimate the aero-optical star centroid error. The method is verified by the Monte Carlo simulation and Hardware-In-Loop simulation. According to Hardware-In-Loop simulation, the star centroid error can be reduced by approximately 27%, and the attitude error can be reduced by approximately 14%. Therefore, the presented method is significant for the application of celestial navigation with hypersonic conditions.
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