Adaptive fault tolerant control method considering input constraints of actuator for hypersonic flight vehicle

A hypersonic, fault-tolerant control technology used in the field of aircraft control

Active Publication Date: 2018-11-30
BEIHANG UNIV
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Problems solved by technology

[0004] The problem to be solved by the technology of the present invention is: because the hypersonic vehicle may be affected by various disturbance factors during flight, which may lead to various failures of the elevator, and the hypersonic vehicle may have actuator input constraint characteristics, the present inven

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  • Adaptive fault tolerant control method considering input constraints of actuator for hypersonic flight vehicle
  • Adaptive fault tolerant control method considering input constraints of actuator for hypersonic flight vehicle
  • Adaptive fault tolerant control method considering input constraints of actuator for hypersonic flight vehicle

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Embodiment Construction

[0077] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.

[0078] Such as figure 1 An adaptive fault-tolerant control method for a hypersonic vehicle considering actuator input constraints is shown. The first step establishes a standard hypersonic vehicle longitudinal dynamics model and decomposes it into velocity, altitude and attitude subsystems; the second step establishes a general aircraft actuator fault model and compensates the actuator by constructing a smooth function In the third step, adaptive compensation controllers and adaptive laws are designed for the three subsystems through dynamic inverse, backstepping and sliding mode control methods. The elevator fault model proposed in the present invention is more general for the representation of faults. By establishing a smooth function to estimate the saturation nonlinearity, the backstepping design method can be used directly. The introduction of t...

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Abstract

The invention relates to an adaptive fault tolerant control method considering input constraints of an actuator for a hypersonic flight vehicle. The method comprises the following steps of firstly, establishing a standard longitudinal dynamics model of the hypersonic flight vehicle and decomposing the model into speed, height and attitude subsystems; secondly, establishing an air vehicle actuatorfault model with generality, and compensating input constraint characteristics of the actuator by constructing a smoothing function; and thirdly, respectively designing an adaptive compensation controller and an adaptive law for three subsystems through a dynamic inverse method, a backstepping method and a sliding mode control method. According to the method, the stability of longitudinal model parameters such as air vehicle speed, height and the like is guaranteed in a level flight working state when the hypersonic flight vehicle with the input constraint characteristics of the actuator has an actuator fault, and the method has the advantages of strong fault-tolerant capability and robustness to external disturbance and the like.

Description

technical field [0001] The invention relates to an adaptive fault-tolerant control method for a hypersonic aircraft considering actuator input constraints, which is mainly used for height and speed tracking when an actuator failure occurs when a hypersonic aircraft is operating in a level flight section and has actuator input constraint characteristics Control belongs to the technical field of aircraft control. Background technique [0002] Hypersonic vehicles have attracted significant commercial and military attention in recent years as a reliable and economical means of transportation to adjacent space. However, due to its special structure and unique flight conditions, hypersonic vehicles are extremely sensitive to aerodynamic parameters and their dynamic characteristics are highly nonlinear. All of these factors make the control design of hypersonic vehicles very difficult compared with traditional aircraft. [0003] So far, control methods including robust control, s...

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/027G05B13/042
Inventor 王陈亮李梓明杨晨
Owner BEIHANG UNIV
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