Nonlinear self-healing control method for multi-sensor fault of hypersonic aircraft

A hypersonic, multi-sensor technology for adaptive control, general control systems, control/regulation systems, etc.

Inactive Publication Date: 2020-04-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] The purpose of the present invention is to provide a non-linear self-healing control method for hypersonic vehicle multi-sensor failure, to solve the problem of fault-tolerant control when the longitudinal system of the hypersonic vehicle suffers from multi-sensor failures in the velocity and angle channels, and improve the system self-healing combined ability

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  • Nonlinear self-healing control method for multi-sensor fault of hypersonic aircraft
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  • Nonlinear self-healing control method for multi-sensor fault of hypersonic aircraft

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[0074] The technical solutions and beneficial effects of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0075] Such as figure 1 As shown, the present invention provides a non-linear self-healing control method for hypersonic vehicle multi-sensor faults. First, a nominal sliding mode controller is designed for the affine nonlinear model obtained through input-output linearization , to track a given reference command; then, aiming at the multi-sensor composite faults that occur in the system, a nonlinear adaptive observer and a backstepping sliding mode observer are designed for the speed and height channels, because the speed channel sensor fault has a great influence on the height channel Due to the coupling effect, the altitude system parameters are changed, which seriously affects the estimation result of the altitude channel sensor fault. Therefore, the backstepping sliding mode observer is used to treat the affected...

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Abstract

The invention discloses a nonlinear self-healing control method for a multi-sensor fault of a hypersonic flight vehicle, and the method comprises the steps: obtaining a longitudinal affine nonlinear system of the hypersonic flight vehicle through employing an input and output feedback linearization technology for a longitudinal nonlinear model of a cruise stage of the hypersonic flight vehicle; establishing a sliding mode surface for the obtained system, and designing a sliding mode controller under a fault-free condition; and injecting a multi-sensor constant deviation fault into an originalhealth system, and designing a fault estimation scheme. Specifically, a nonlinear adaptive observer is designed for a speed channel; aiming at a height channel, a backstepping sliding mode observer isdesigned to estimate a state quantity and a sensor fault; and after a fault estimation result of the height sensor and the speed sensor is obtained, a fault-tolerant controller is designed to compensate output signals of the height sensor and the speed sensor. The method can solve the problem of fault-tolerant control under the condition that the longitudinal system of the hypersonic aircraft suffers from speed and angle channel multi-sensor faults, and the self-healing capacity of the system is improved.

Description

technical field [0001] The invention belongs to the technical field of fault-tolerant control of hypersonic aircraft sensors, and in particular relates to a nonlinear self-healing control method for multi-sensor faults of hypersonic aircraft. Background technique [0002] In recent years, due to the many advantages of hypersonic vehicles in military and civilian aspects such as launch cost, flight speed, space transportation and global strike, they have attracted much attention. Compared with traditional aerospace vehicles, hypersonic vehicles have dynamic characteristics such as strong nonlinearity, strong coupling and fast time-varying. The conditions of atmospheric density, temperature and airflow environment in near space are more complex and harsh than the flight environment of ordinary aircraft. The sensor system is easily affected by freezing, high temperature and lightning, causing failures, deviations in measured values, and even errors in the overall measurement of...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 陈复扬张启航李雨清刘宇曦牛娟
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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