Discrete sliding mode intelligent control method for aircraft based on time-varying sliding mode gain

A technology of intelligent control and intelligent controller, applied in the field of aircraft control, can solve problems such as poor practicability, and achieve the effects of facilitating engineering application, improving learning accuracy, and reducing chattering

Active Publication Date: 2022-03-29
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

[0006] In order to overcome the shortcomings of poor practicability of existing discrete control methods for aircraft, the present invention provides a discrete sliding mode intelligent control method for aircraft based on time-varying sliding mode gain

Method used

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  • Discrete sliding mode intelligent control method for aircraft based on time-varying sliding mode gain
  • Discrete sliding mode intelligent control method for aircraft based on time-varying sliding mode gain
  • Discrete sliding mode intelligent control method for aircraft based on time-varying sliding mode gain

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Embodiment Construction

[0159] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0160] refer to figure 1 , the present invention is based on the aircraft discrete sliding mode intelligent control method of time-varying sliding mode gain. The specific steps are as follows:

[0161] Step 1: Consider the vehicle longitudinal channel dynamics model:

[0162]

[0163]

[0164]

[0165]

[0166]

[0167] Among them, X s =[V,h,α,γ,q] T is the state variable, U c =[δ e ,β] T is the control input; V is the speed, γ is the track inclination, h is the altitude, α is the angle of attack, q is the pitch angle velocity, δ e Indicates the rudder deflection angle, β indicates the throttle valve opening; T, D, L and M yy represent thrust, drag, lift and pitching moment respectively; m, I yy , μ and r respectively represent the mass, the moment of inertia of the pitch axis, the gravitational coefficient and the distance from the center ...

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Abstract

The invention relates to an aircraft discrete sliding mode intelligent control method based on time-varying sliding mode gain, which is used to solve the technical problem of poor practicability of the existing aircraft discrete control method. By performing Euler discretization on the longitudinal channel dynamics model of the aircraft, the discrete form of the original system is obtained; considering the causal relationship of the system, an equivalent prediction model of the attitude discrete strict feedback system is established; the unknown nonlinear function of the system is approximated by neural network, based on Neural network identification error design controller sliding mode time-varying gain and neural network weight vector update law; the introduction of neural network intelligent learning offsets the upper and lower bounds of uncertain items, reduces the amplitude of sliding mode switching chattering, and improves sliding The performance of model control; the present invention combines the characteristics of computer control, and the controller designed through model conversion effectively avoids non-causal problems, and is suitable for engineering applications.

Description

technical field [0001] The invention belongs to the field of aircraft control, in particular to an aircraft discrete sliding mode intelligent control method based on time-varying sliding mode gain. Background technique [0002] In actual engineering, with the development of computer technology, many high-performance aircraft are equipped with computer systems, and most of their control tasks need to be realized by onboard computers. Therefore, the study of advanced control methods in discrete situations is of great significance to the research of aircraft control. And there is an urgent need. [0003] The design of discrete controllers usually adopts two methods: 1) first design the controller according to the continuous control object, and then discretize the continuous controller; 2) design the discrete controller directly according to the discrete control object. The first method requires a faster sampling rate and requires higher system hardware. In actual engineering,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌程怡新杨舒梁捷
Owner NORTHWESTERN POLYTECHNICAL UNIV
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