Journal of Astronautics ›› 2019, Vol. 40 ›› Issue (11): 1332-1340.doi: 10.3873/j.issn.1000-1328.2019.11.009

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Attitude Maneuvering Trajectory Design and Tracking Control for Flexible Spacecraft

ZHANG Xiu yun, ZONG Qun, ZHU Wan wan, LIU Wen jing   

  1. 1. School of Electrical and Information Engineering, Tianjin University, Tianjin 300072, China; 2. Beijing Institute of Control
    Engineering, Beijing 100190, China
  • Received:2018-10-08 Revised:2019-03-26 Online:2019-11-15 Published:2019-11-25

Abstract: For the contradiction between “rapidity” and “stability” of the attitude maneuvering of a flexible spacecraft, an integrated method of optimization and control for the attitude maneuvering trajectory design and tracking control is proposed in this paper. Firstly, considering the rapidity and stability requirements of the flexible spacecraft’s attitude maneuvering, the multi-objective and multi-constraint conditions are established, and the attitude trajectory is acquired by optimization, which can maximize the system stability while considering the performance of rapidity. Then, a novel fast robust input shaper(FRIS) is designed. It could suppress the vibration effectively and the action time is shorter than a traditional input shaper, which is beneficial for the rapidity and high precision. Finally, a novel adaptive continuous terminal sliding mode controller(ACTSMC) is proposed, which can avoid gain over-estimation, and guarantee the fast and high-precision tracking control of the desired attitude trajectory. The numerical simulations have demonstrated the effectiveness of the approach proposed.

Key words:  Flexible spacecraft, Trajectory optimization, Fast robust input shaper (FRIS), Attitude maneuver control, Active vibration suppression

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