This work investigates the anti-saturation attitude tracking control for the tailless aircraft with guaranteed output constraints, in presence of uncertain inertia parameters, bounded external disturbance, and actuator faults/failures. A predefined-time adaptive backstepping attitude control scheme has been proposed, the main features of this scheme lie in (a) designing a predefined-time filter to deal with the 'explosion of complexity' and singularity problem; (b) introducing a nonlinear state-dependent function to handle the asymmetric time-varying output constraints; (c) compensating for the impact of the actuator faults/failures and input saturation by a nonlinear function and bounded estimation simultaneously. Moreover, the proposed control scheme can ensure all signals in the closed-loop system converge to a residual set around the origin within a predefined time, and this time constant can be set freely by the designer, independently of initial conditions. Article Finally, numerical simulations have been conducted to verify the performance of the proposed predefined-time fault-tolerant control scheme.
This article investigates the fault-tolerant attitude control problem for the tailless flying wing aircraft subject to time-varying flight envelope constraints in the presence of the matched/mismatched disturbance, uncertain parameters, and time-varying actuator failures. To handle these problems and improve the convergence rate of the attitude control system, a nonsingular fixed-time convergent robust fault-tolerant control methodology is proposed. First, the time-varying barrier Lyapunov functions is introduced to confine the flight envelope within the predefined time-varying compact set while ensuring the transient performance of the attitude tracking error. Subsequently, the fixed-time sliding mode observer is designed to compensate for the matched/mismatched disturbance, uncertainties, and time-varying actuator failures, meanwhile, by introducing an intermediate control law in the attitude controller, the singularity problem is avoided without utilizing any filters or continuous and differentiable piecewise functions. Further, it has been analytically proved that all signals of the closed-loop system are bounded and converge to the residual set around the origin in a fixed time. Finally, simulations are conducted to illustrate the superiorities of the proposed scheme.
This work investigates the anti-saturation attitude tracking control for the tailless aircraft with guaranteed output constraints, in presence of uncertain inertia parameters, bounded external disturbance, and actuator faults/failures. A predefined-time adaptive backstepping attitude control scheme has been proposed, the main features of this scheme lie in (a) designing a predefined-time filter to deal with the `explosion of complexity' and singularity problem; (b) introducing a nonlinear state-dependent function to handle the asymmetric time-varying output constraints; (c) compensating for the impact of the actuator faults/failures and input saturation by a nonlinear function and bounded estimation simultaneously. Moreover, the proposed control scheme can ensure all signals in the closed-loop system converge to a residual set around the origin within a predefined time, and this time constant can be set freely by the designer, independently of initial conditions. Finally, numerical simulations have been conducted to verify the performance of the proposed predefined-time fault-tolerant control scheme.
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