High-Precison In-flight Attitude Estimation Algorithm For Missile

A nonlinear inertial navigation system (INS) attitude estimation method is proposed, which is based on the modified-Rodrigues parameter. The close-loop Kalman Filter is designed to achieve the full-attitude and non-singular attitude estimation, with the satellite navigation data used as the observab...

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Bibliographic Details
Published in2021 40th Chinese Control Conference (CCC) pp. 3605 - 3609
Main Authors Xie, Jia, Gong, YingHui, Chen, Fang, Guo, ZhenXi, Zhang, JianFei, Tang, Mao
Format Conference Proceeding
LanguageEnglish
Published Technical Committee on Control Theory, Chinese Association of Automation 26.07.2021
Subjects
Closed-loop estimation
Estimation
Filtering
Filtering algorithms
In-flight alignment
Inertial navigation
Kalman filter
Missiles
Modified-Rodrigues parameter
Quaternions
Satellites
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Summary:A nonlinear inertial navigation system (INS) attitude estimation method is proposed, which is based on the modified-Rodrigues parameter. The close-loop Kalman Filter is designed to achieve the full-attitude and non-singular attitude estimation, with the satellite navigation data used as the observable quantity. The accuracy of the proposed method is higher than the traditional attitude estimation method using misalignment angle and quaternion error.
ISSN:2161-2927
DOI:10.23919/CCC52363.2021.9550540