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This paper tackles the attitude cooperative control problem of multi-spacecraft systems in complex environments for space missions. A predefined-performance-based attitude cooperative control method is presented based on terminal sliding mode. By leveraging the finite-time convergence and strong robustness of terminal sliding mode, the proposed method enhances the spacecraft coordination ability in dealing with model uncertainties and external disturbances. Meanwhile, a predefined performance function is introduced to dynamically constrain the attitude coordination errors, ensuring that the control process meets predefined performance criteria and thereby improving the overall coordination performance of the multi-spacecraft systems. Simulations are conducted on a system comprising five simulated spacecraft, demonstrating rapid convergence of both attitude and angular velocity errors. The theoretical results validate the effectiveness of the presented method.

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Multi-spacecraft Attitude Coordination Based on Performance-Constrained Terminal Sliding Mode Control

  • 会议论文

  • 发表日期：

    2026年

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  • Yongjie Zeng,
  • Fusheng Hou,
  • Jiayang Li,
  • Yabin Gao

摘要

This paper tackles the attitude cooperative control problem of multi-spacecraft systems in complex environments for space missions. A predefined-performance-based attitude cooperative control method is presented based on terminal sliding mode. By leveraging the finite-time convergence and strong robustness of terminal sliding mode, the proposed method enhances the spacecraft coordination ability in dealing with model uncertainties and external disturbances. Meanwhile, a predefined performance function is introduced to dynamically constrain the attitude coordination errors, ensuring that the control process meets predefined performance criteria and thereby improving the overall coordination performance of the multi-spacecraft systems. Simulations are conducted on a system comprising five simulated spacecraft, demonstrating rapid convergence of both attitude and angular velocity errors. The theoretical results validate the effectiveness of the presented method.