4.6 Article

Robust extended Kalman filter with input estimation for maneuver tracking

期刊

CHINESE JOURNAL OF AERONAUTICS
卷 31, 期 9, 页码 1910-1919

出版社

ELSEVIER SCIENCE INC
DOI: 10.1016/j.cja.2018.06.014

关键词

Extended Kalman filters; Input estimation; Maneuver detection; Maneuver tracking; Orbit determination

资金

  1. National Natural Science Fund for Distinguished Young Scholars of China [11525208]

向作者/读者索取更多资源

This study investigates the problem of tracking a satellite performing unknown continuous maneuvers. A new method is proposed for estimating both the state and maneuver acceleration of the satellite. The estimation of the maneuver acceleration is obtained by the combination of an unbiased minimum-variance input and state estimation method and a low-pass filter. Then a threshold-based maneuver detection approach is developed to determinate the start and end time of the unknown maneuvers. During the maneuvering period, the estimation error of the maneuver acceleration is modeled as the sum of a fluctuation error and a sudden change error. A robust extended Kalman filter is developed for dealing with the acceleration estimate error and providing state estimation. Simulation results show that, compared with the Unbiased Minimum-variance Input and State Estimation (UMISE) method, the proposed method has the same position estimation accuracy, and the velocity estimation error is reduced by about 5 times during the maneuver period. Besides, the acceleration detection and estimation accuracy of the proposed method is much higher than that of the UMISE method. (C) 2018 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.

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