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Fault-tolerant control method for hypersonic aircraft elevator with state limitation

A hypersonic, fault-tolerant control technology, applied in general control systems, control/regulation systems, test/monitoring control systems, etc., can solve problems such as reducing system accuracy, ignoring the coupling of speed subsystems and altitude subsystems

Active Publication Date: 2019-09-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, both of the aforementioned papers ignore the coupling of velocity and altitude subsystems
the dynamics of hypersonic vehicles are characterized by strong coupling, therefore, ignoring the coupling between height dynamics and velocity dynamics may reduce the accuracy of the system

Method used

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  • Fault-tolerant control method for hypersonic aircraft elevator with state limitation
  • Fault-tolerant control method for hypersonic aircraft elevator with state limitation
  • Fault-tolerant control method for hypersonic aircraft elevator with state limitation

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Embodiment Construction

[0061] Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0062] like figure 1 As shown, the present invention provides a method for controlling elevator failure of hypersonic aircraft, comprising the following steps:

[0063] Step 1, establish the longitudinal kinematics and dynamics model of the cruise segment of the hypersonic vehicle, the model is expressed as:

[0064]

[0065]

[0066]

[0067]

[0068]

[0069]

[0070] where V, γ, h, α, q, ζ i Respectively represent the velocity, track angle, height, attack angle, pitch rate and elastic variable of the hypersonic vehicle; L, D, T are the lift, drag and thrust respectively; m, μ, r represent the mass and gravitational constant of the vehicle , the di...

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Abstract

The invention discloses a fault-tolerant control method for a hypersonic aircraft elevator with state limitation. For the longitudinal model of a hypersonic aircraft, an adaptive fault-tolerant controller is proposed to realize state constraint under consideration of the internal coupling of a system. The complexity caused by aerodynamic uncertainty, external disturbances and elastic modes is considered throughout the controller design process. The method comprises the steps that a sliding mode control method is introduced in the first step of a backstepping process to handle the coupling of the system; the obstacle Lyapunov function is applied to the subsequent backstepping process to ensure that the angle of attack and pitch rate are limited; moreover, due to the introduction of the dynamic surface method, the problem of differential explosion is avoided; and finally, the fault-tolerant controller structure is designed for the unknown fault of the elevator. According to the invention, the coupling problem and the state limitation problem of the system can be simultaneously handled, and the accuracy of the control system is improved.

Description

technical field [0001] The invention relates to a hypersonic vehicle elevator fault-tolerant control method with state limitation, and belongs to the technical field of automatic control. Background technique [0002] Hypersonic vehicles are by far the most complex flight process, and have many different flight characteristics compared with subsonic / supersonic vehicles. Due to the large-scale changes in working conditions, the huge difference in the aerodynamic characteristics of hypersonic vehicles at high and low altitudes, and the rapid changes in mass distribution, the dynamic characteristics and model parameters of hypersonic vehicles change significantly during flight. The integrated configuration of the engine and the fuselage results in a strong coupling between the elastic fuselage, propulsion system, and structural dynamics, resulting in very complex flight dynamics characteristics of hypersonic vehicles and great uncertainty. At the same time, the state of hypers...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0286
Inventor 齐瑞云彭志宇姜斌孟亦真董旺唐建
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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