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<p>This paper focuses on the issue of high-precision attitude tracking in rigid spacecraft systems under state constraints, parameter uncertainties, external disturbances, and actuator failures. For this purpose, based on the Newton-Euler model for the unit quaternion method, an attitude-tracking transformation equation is constructed to satisfy the enhanced predefined-time performance function (E-PTPF) under the prescribed performance attitude-tracking error, wh-ich can not only adjust the shape and rate according to the actual situation, but also reduce the overshoot. Then, a nonsingular predefined-time sliding mode surface (NPTSMS) method is designed by the transformation model. A nonsingular adaptive fault-tolerant predefined-time controller (NAFTPTC) not only effectively solves the potential chattering problem during controller design, but also ensures the state error constraints and attitude stable performances. Simulation comparison results confirm the efficacy of the designed controller method under multiple types of faults.</p>

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Constrained nonsingular predefined-time fault-tolerant control with prescribed performance for rigid spacecraft

  • 期刊论文

  • 发表日期：

    2025年6月24日

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  • Meiling Tao,
  • Wuhao Fang,
  • Shengping Luo,
  • Shuai Zhang

摘要

This paper focuses on the issue of high-precision attitude tracking in rigid spacecraft systems under state constraints, parameter uncertainties, external disturbances, and actuator failures. For this purpose, based on the Newton-Euler model for the unit quaternion method, an attitude-tracking transformation equation is constructed to satisfy the enhanced predefined-time performance function (E-PTPF) under the prescribed performance attitude-tracking error, wh-ich can not only adjust the shape and rate according to the actual situation, but also reduce the overshoot. Then, a nonsingular predefined-time sliding mode surface (NPTSMS) method is designed by the transformation model. A nonsingular adaptive fault-tolerant predefined-time controller (NAFTPTC) not only effectively solves the potential chattering problem during controller design, but also ensures the state error constraints and attitude stable performances. Simulation comparison results confirm the efficacy of the designed controller method under multiple types of faults.