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In this paper, a composite adaptive predefined-time fault-tolerant attitude control strategy is proposed for rigid spacecraft with external disturbances, inertia uncertainties, and actuator faults. By establishing a practical predefined-time stability criterion, a predefined-time controller is systematically presented, allowing the upper bound of spacecraft settling time to be precisely determined by adjusting only one control parameter. To accurately compensate for lumped uncertainty, two adaptive update laws are designed. In addition, the singularity problem can be effectively avoided by constructing the hyperbolic tangent function. The efficacy of the proposed control strategy is verified through numerical simulations.

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Composite Adaptive Predefined-Time Fault-Tolerant Attitude Control for Rigid Spacecraft

  • 会议论文

  • 发表日期：

    2026年

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  • Shuzong Xie,
  • Huihui Shi,
  • Xudong Gao,
  • Jianwei Dong,
  • Jun Yang,
  • Beiping Hou

摘要

In this paper, a composite adaptive predefined-time fault-tolerant attitude control strategy is proposed for rigid spacecraft with external disturbances, inertia uncertainties, and actuator faults. By establishing a practical predefined-time stability criterion, a predefined-time controller is systematically presented, allowing the upper bound of spacecraft settling time to be precisely determined by adjusting only one control parameter. To accurately compensate for lumped uncertainty, two adaptive update laws are designed. In addition, the singularity problem can be effectively avoided by constructing the hyperbolic tangent function. The efficacy of the proposed control strategy is verified through numerical simulations.