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Time-varying-sliding-mode-gain-based aircraft discrete sliding-mode intelligent control method

A technology of time-varying gain and intelligent control, which is applied in the field of aircraft control and can solve problems such as poor practicability

Active Publication Date: 2019-10-25
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

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  • Time-varying-sliding-mode-gain-based aircraft discrete sliding-mode intelligent control method
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  • Time-varying-sliding-mode-gain-based aircraft discrete sliding-mode intelligent control method

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Embodiment Construction

[0159] The present invention will now be further described in conjunction with the embodiments and drawings:

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

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

[0162]

[0163]

[0164]

[0165]

[0166]

[0167] Where X s =[V,h,α,γ,q] T Is the state variable, U c =[δ e ,β] T Is the control input; V means speed, γ means track inclination, h means altitude, α means angle of attack, q means pitch speed, δ e Indicates rudder deflection angle, β represents throttle opening; T, D, L and M yy Respectively represent thrust, drag, lift and pitch rotation moment; 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 of the earth;

[0168] The torque and parameters of the...

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Abstract

The invention relates to a time-varying-sliding-mode-gain-based aircraft discrete sliding-mode intelligent control method, thereby solving a technical problem of poor practicability of the existing aircraft discrete control method of the aircraft. Euler discretization is performed by using a longitudinal channel dynamics model of an aircraft to obtain a discrete form of an original system; with consideration of the system causality, an equivalent prediction model of an attitude discrete strict feedback system is established; and approximation to a system unknown nonlinear function is performedby using a neural network and an error design controller sliding-mode time-varying gain and a neural network weight vector update law are identified by using the neural network. With introduction ofthe neural network intelligent learning, upper and lower bounds of uncertainties can be cancelled, the amplitude of sliding-mode switching chattering can be reduced, and the performance of the slidingmode control can be improved. On the basis of combination of characteristics of the computer control, the non-causal problem is solved effectively by using the controller based on the model conversion design. The method is suitable for the engineering application.

Description

Technical field [0001] The invention belongs to the field of aircraft control, and in particular relates 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 airborne 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 controller 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 engineer...

Claims

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Application Information

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Patent Type & Authority Applications(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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