Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (9): 927-935.doi: 10.3873/j.issn.1000-1328.2017.09.005

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On Orbit Identification of the Moment of Inertia for a Spacecraft with Flexible Appendages during a Large Angle Maneuver

HE Xiao, TAN Shu jun, WU Zhi gang   

  1. 1. School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024,China;
    2. State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian 116024,China
  • Received:2017-01-19 Revised:2017-06-22 Online:2017-09-15 Published:2017-09-25


For the problem of the on-orbit identification of the moment of inertia for a spacecraft with flexible appendages during a large-angle maneuver, a concurrent recursive algorithm is proposed in this paper, which combines the estimation of the inertia parameters with the state estimation of the flexible appendages’ vibration modes. The algorithm is based on the nonlinear dynamic model of a spacecraft with flexible appendages during a large-angle maneuver. The extended Kalman filter is used to estimate the states of the flexible appendages’ vibration modes, and the least square method is used to estimate the parameters of the moment of inertia. Finally, the inertia parameters of the spacecraft are obtained by the concurrent recursive algorithm. In order to improve the efficiency of the algorithm, a recursive algorithm based on one-step least square method and multi-step extended Kalman filter is proposed. Simulation results show that the proposed algorithm not only improves the computational accuracy and efficiency, but also has the capability of anti-interference.

Key words: Flexible appendages, Moment of inertia, On orbit parameter identification, Extended Kalman filter (EKF), Least square

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