Abstract
In this paper, an adaptive finite-time fault-tolerant control scheme is proposed for the attitude stabilization of rigid spacecrafts. A first-order command filter is presented at the second step of the backstepping design to approximate the derivative of the virtual control, such that the singularity problem caused by the differentiation of the virtual control is avoided. Then, an adaptive fuzzy finite-time backstepping controller is developed to achieve the finite-time attitude stabilization subject to inertia uncertainty, external disturbance, actuator saturation, and faults. Through using an error transformation, the prescribed performance boundary is incorporated into the controller design to guarantee the prescribed performance of the system output. Numerical simulations demonstrate the effectiveness of the proposed scheme.
Highlights
Due to the significant role in guaranteeing the success of any spacecraft related mission, the attitude control of the spacecraft has obtained much attention, and numerous control schemes are proposed, such as adaptive control, sliding mode control, backstepping control, H∞ control, finite-time control, and so on [1,2,3,4,5,6,7,8]
The active faulttolerant control (FTC) relies on the fault detection and diagnosis (FDD) algorithm to provide the real-time information of the system status and reconfigure the controller to achieve the control objective
The control objective in this paper is to develop a fuzzy fault-tolerant finite-time control scheme for the spacecraft with inertia uncertainty, extra disturbance, input saturation, and actuator faults, such that the system output σ converges into a small region of the origin within the prescribed bounds in a finite time
Summary
Due to the significant role in guaranteeing the success of any spacecraft related mission, the attitude control of the spacecraft has obtained much attention, and numerous control schemes are proposed, such as adaptive control, sliding mode control, backstepping control, H∞ control, finite-time control, and so on [1,2,3,4,5,6,7,8]. In [12], a fault-tolerant control method based on distribution matrix was presented for the spacecraft attitude tracking, such that the finite-time convergence of the tracking error was achieved. Actuator saturation is another issue worthy of study, the actual actuators in the spacecraft have the nominal limit of the output, and saturated output definitely effaces the system performance. Motivated by the aforementioned discussions, the fuzzy finite-time attitude stabilization problem for spacecraft systems under the actuator saturation and faults is studied in this paper, and a fuzzy finite-time fault-tolerant controller is proposed to achieve prescribed transient and steadystate performance of the system output.
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