Abstract
This paper provides a solution for the trajectory tracking control of a hypersonic flight vehicle (HFV), which is encountered performance constraints, actuator faults, external disturbances, and system uncertainties. For the altitude and velocity control subsystems, the backstepping-based dynamic surface control (DSC) strategy is constructed to guarantee the predefined constraint of tracking errors. The introduction of first-order low-pass filters effectively remedies the problem of “complexity explosion” existing in high-order backstepping design. Simultaneously, radial basis function neural networks (RBFNNs) are adopted for approximating the unavailable dynamics, in which the minimum learning parameter (MLP) algorithm brilliantly alleviates the excessive occupation of the computational resource. Specially, in consideration of the unknown actuator failures, the adaptive signals are designed to enhance the reliability of the closed-loop system. Finally, according to rigorous theoretical analysis and simulation experiment, the stability of the proposed controller is verified, and its superiority is exhibited intuitively.
Highlights
The recent few years have witnessed the burgeoning interest in hypersonic flight vehicles (HFVs) from researchers owing to its unique advantages like rapid maneuver and high efficiency
Driven by the aforementioned observations, this paper aims at the prescribed performance fault-tolerant control for HFV suffering from system uncertainties and actuator failures
For the HFV system (24), if the virtual commands are designed as Equations (31), (35), and (40), control signals are designed as Equations (45)–(47); it can be concluded that the tracking errors satisfy exponential convergence, and the prescribed performance constraints are guaranteed
Summary
The recent few years have witnessed the burgeoning interest in hypersonic flight vehicles (HFVs) from researchers owing to its unique advantages like rapid maneuver and high efficiency. While accounting for the uncertainties of HFV models, great demands were placed on the International Journal of Aerospace Engineering convergence rate and tracking accuracy of control systems [18] From this view of point, most of the aforementioned controllers possess satisfactory steady-state characteristics but lack specific constraints on transient performances. The computational complexity is considerably degraded, and the hardware requirement is reduced significantly (2) In [23, 24], PPC control methods were presented for MEMS Gyroscopes and Networked Uncertain Quadrotors, respectively, which cannot be directly applied for hypersonic vehicles Considering this point, the PPC-based dynamic surface controller is synthesized for hypersonic vehicles in the presence of uncertainties, actuator faults, and disturbances.
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