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Singular perturbation composite learning control method of elastic aircraft based on interference observation

A singular perturbation and learning control technology, applied in the field of aircraft control, can solve problems such as the inability to guarantee the system control accuracy, the decline of the system control accuracy, and the breakage of the body.

Inactive Publication Date: 2019-10-11
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

[0002] Due to the use of lightweight materials, the aircraft has structural elasticity problems, which will not only lead to a decrease in the control accuracy of the system, but may also cause the fuselage to break
At the same time, due to the complexity of the flight environment and system structure, the aircraft dynamics model has unknown nonlinearity, the intelligent control technology based on the neural network has received widespread attention, but most of the existing intelligent approximation methods are only based on the Lyapunov stability design weight update law , the lack of mining of internal information violates the original intention of effectively estimating unknown dynamics
"Robust adaptive neural control of flexible hypersonicflight vehicle with dead-zone input nonlinearity" (Bin Xu, "NonlinearDynamics", 2015, 80:1509-1520) regards the elastic mode as a disturbance item, and uses the robust item to control the elastic mode Compensation solves the problem of elastic body control of hypersonic vehicles, but this method does not conduct in-depth analysis and processing of elastic modes, and does not consider the influence of external disturbances on the system, so the control accuracy of the system cannot be guaranteed

Method used

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  • Singular perturbation composite learning control method of elastic aircraft based on interference observation
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  • Singular perturbation composite learning control method of elastic aircraft based on interference observation

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Embodiment Construction

[0123] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0124] refer to figure 1 , the invention's singular perturbation compound learning control method for elastic aircraft based on disturbance observation is applied to a class of elastic hypersonic aircraft, and is realized by the following steps:

[0125] (a) Consider the dynamic model of the longitudinal channel of the elastic vehicle:

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[0132] The kinematic model is composed of seven state quantities and two control inputs U=[δ e ,Φ] T composition. Among them, V represents velocity, h represents height, γ represents track inclination, α represents angle of attack, q represents pitch angle velocity, η and Indicates the elastic mode, δ e Indicates rudder deflection angle, Φ indicates throttle valve opening; d γ 、d θ and d q Indicates unknown external interference; m, I yy and g den...

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Abstract

The invention relates to a singular perturbation composite learning control method of an elastic aircraft based on interference observation. According to the method, a longitudinal channel model of the elastic aircraft is decomposed into a speed subsystem and a posture subsystem at first; and PID control is adopted for the speed subsystem, the posture subsystem is analyzed by using the singular perturbation theory, and rigid-flexible mode decoupling and fast and slow time scale separation are realized. A sliding mode control method is designed to control an elastic fast-changing subsystem; anda back stepping method is designed to control a posture slow change subsystem, meanwhile unknown dynamics is approached by using a composite neural network, and a nonlinear observer is designed to compensate the external disturbances. Based on the controller designed above, precise tracking of height and speed is achieved.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to a singular perturbation compound learning control method for an elastic aircraft based on disturbance observation, and belongs to the field of aircraft control. Background technique [0002] Due to the use of lightweight materials, the aircraft has structural elasticity problems, which will not only lead to a decrease in the control accuracy of the system, but may also cause the fuselage to break. At the same time, due to the complexity of the flight environment and system structure, the aircraft dynamics model has unknown nonlinearity, the intelligent control technology based on the neural network has received widespread attention, but most of the existing intelligent approximation methods are only based on the Lyapunov stability design weight update law , the lack of mining of internal information violates the original intention of effectively estimating unknown dynamics. "Robust ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42G05B13/04G05D1/08G05D1/04G05D13/62
CPCG05B11/42G05B13/027G05B13/042G05D1/0825G05D1/042G05D13/62
Inventor 许斌王霞梁捷袁源
Owner NORTHWESTERN POLYTECHNICAL UNIV
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