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Volume 49 Issue 5
May  2023
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Journal of Beijing University of Aeronautics and Astronautics  > 2023  >  49(5): 1222-1230.
HE J J，YUAN C Q，GONG S P，et al. Sliding mode control for formation flying near libration points using hybrid propulsion[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（5）：1222-1230 （in Chinese） doi: 10.13700/j.bh.1001-5965.2021.0420
Citation: HE J J，YUAN C Q，GONG S P，et al. Sliding mode control for formation flying near libration points using hybrid propulsion[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（5）：1222-1230 （in Chinese） doi: 10.13700/j.bh.1001-5965.2021.0420
shu

Sliding mode control for formation flying near libration points using hybrid propulsion

doi: 10.13700/j.bh.1001-5965.2021.0420
  • 1.

    School of Aviation Operations and Services，Air Force Aviation University，Changchun 130011，China

  • 2.

    School of Aviation Fundamentals，Air Force Aviation University，Changchun 130011，China

  • 3.

    School of Astronautics，Beihang University，Beijing 100191，China

More Information
  • Corresponding author: E-mail: ycq02@mails.tsinghua.edu.cn
  • Received Date: 26 Jul 2021
  • Accepted Date: 11 Oct 2021
    • Available Online: 02 Jun 2023
  • Publish Date: 04 Nov 2021
    Abstract

  • Abstract: Aiming at the flight control problem of proximity spacecraft formation near the artificial L1point of the sun-earth system, a hybrid propulsion control method combining solar sail propulsion and Coulomb force formation technology is proposed. By controlling the relative attitude angles of the follower’s sail, the solar radiation pressure difference between two spacecraft can be adjusted, and matched with Coulomb force, not only the underactuated problem of solar sail control alone is solved, but the controllability of Coulomb formation is also improved. Firstly, based on the solar sail circular restricted three-body problem (SSCRTBP) model, the calculation method of the position of the collinear artificial libration point is given and the orbit of the main craft is constructed. The relative motion equation of the hybrid propulsion configuration is then determined by the introduction of the Coulomb force between spacecraft. Finally, the fixed-time sliding mode control strategy is designed to control the formation configuration by taking the two attitude angles of the follower’s sail and the charge product between the two crafts as the control parameters. Then the sliding mode control strategy is compared with the LQR control strategy in order to reflect its high performance. The simulation results show that the fixed-time sliding mode control strategy is superior to the LQR control strategy in terms of control accuracy, required time and energy consumption. During a 3-year mission, the formation can be deployed in only 23 days. The baseline relative error is less than 1%, whereas the error on the other two axes is on the scale of centimeters. For long-term deep space exploration trips in the future, the fact that no fuel is used throughout the entire process is extremely important.

     

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