کنترل تحمل‌‌پذیر خطای فعال مود لغزشی ترمینال سریع غیرتکین تطبیقی مبتنی بر مشاهده‌گر یادگیری فضاپیمای انعطاف‌پذیر

This study introduces an active fault - tolerant control algorithm designed to simultaneously suppress the vibration and control the attitude of a rigid - flexible spacecraft equipped with sensor/actuator patches. The control method, based on a fast, non singular terminal sliding mode adaptive strategy, ensures fixed time convergence and effectively mitigates singularity issues. The proposed controller, utilizing adaptive parameters, is robust to inertia uncertainties and external disturbances. Furthermore, a learning observer is employed to estimate rigid body actuator faults, providing enhanced accuracy with minimal computational burden. To minimize vibrations arising from attitude dynamics and actuator faults, an active vibration control algorithm base on strain rate feedback (SRF) approach is simultaneously deployed throughout the flexible spacecraft attitude maneuver. The stability of the closed - loop system is verified using the Lyapunov theorem. Simulations are conducted to evaluate the proposed method’s performance, fault tolerance, and its effect on the system structural flexibility.