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Acta Aeronautica et Astronautica Sinica ›› 2024, Vol. 45 ›› Issue (16): 329678-329678.doi: 10.7527/S1000-6893.2024.29678

• Electronics and Electrical Engineering and Control • Previous Articles    

State and bias estimation of spacecraft attitude control system based on l1-TSXKF

Xueqin CHEN1, Boyu YANG1, Fan WU1(), Chengfei YUE2, Xibin CAO1   

  1. 1.Research Center of Satellite Technology,Harbin Institute of Technology,Harbin  150001,China
    2.Institute of Space Science and Applied Technology,Harbin Institute of Technology (Shenzhen),Shenzhen  518055,China
  • Received:2023-10-07 Revised:2023-12-21 Accepted:2024-01-05 Online:2024-01-16 Published:2024-01-15
  • Contact: Fan WU E-mail:wufanrcst@hit.edu.cn
  • Supported by:
    National Natural Science Foundation of China(11972130);Heilongjiang Touyan Innovation Team Program

Abstract:

The state and bias estimation problem of spacecraft attitude control system considering non-Gaussian noise characteristics is studied. Firstly, a spacecraft attitude control system model with bias is established, and the expression for the non-Gaussian characteristic noise is given. Then, through l1-norm Kalman Filtering (l1-KF) algorithm and mathematical simulation, it is verified that the introduction of l1-norm into the Kalman filtering algorithm can avoid the influence of non-Gaussian process noise. However, the l1-KF algorithm cannot achieve simultaneous estimation of state and bias, and is only suitable for estimation of attitude stability control process. Therefore, on the basis of l1-KF algorithm, considering the complex situation of time-varying moment of inertia and time-varying bias of the system, as well as real-time identification of time-varying moment of inertia, an l1-norm Two-Stage eXogenous Kalman Filtering (l1-TSXKF) algorithm is designed to estimate the state and bias of the spacecraft during attitude maneuver. The mathematical simulation results show that the l1-TSXKF algorithm can reduce the influence of non-Gaussian characteristics of the system and obtain high precision attitude and bias estimation results quickly in the process of spacecraft attitude maneuver, which is conducive to the application of spacecraft in orbit.

Key words: spacecraft, attitude control system, bias estimation, state estimation, identification of moments of inertia

CLC Number: