Aircraft channel coupling coordination control method based on data analysis

A technology of coordinated control and data analysis, applied in the field of flight control, to achieve the effect of coordinated control

Active Publication Date: 2021-02-05
NORTHWESTERN POLYTECHNICAL UNIV +1
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem of efficient utilization of channel coupling and unknown dynamics of the system in the process of aircraft reentry, the present invention proposes a data analysis-based aircraft channel coupling coordination control method

Method used

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  • Aircraft channel coupling coordination control method based on data analysis
  • Aircraft channel coupling coordination control method based on data analysis
  • Aircraft channel coupling coordination control method based on data analysis

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Embodiment Construction

[0052] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0053] refer to figure 1 , the present invention is a kind of aircraft channel coupling coordination control method based on data analysis, realizes by following steps:

[0054] (a) Using the aircraft re-entry segment dynamics model:

[0055]

[0056] ω=-J -1 ΩJω+J -1 m c (16)

[0057] The dynamic model contains two state variables X=[γ,ω] T and a control input M c ;where, γ=[σ,β,α] T represents the attitude angle vector, σ represents the tilt angle, β represents the sideslip angle, α represents the attack angle, ω=[ω x ,ω y ,ω z ] T Represents the attitude angular rate vector of the aircraft, ω x represents the roll rate, ω y Indicates the yaw rate, ω z Indicates pitch rate, M c =[M x , M y , M z ] T Indicates the control torque of the system, M x Indicates the rolling moment, M y Indicates the yaw moment, M z Indicates the pitching mom...

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Abstract

The invention relates to an aircraft channel coupling coordination control method based on data analysis, and the method comprises the steps: defining three layers of sliding mode surfaces based on akinetic model of an aircraft reentry section and the characteristics of an analysis model, designing an equivalent control law through employing a Filippov equivalent theory, and designing a switchingcontrol law through employing a sliding mode control principle; utilizing unknown dynamics of a neural network estimation system, constructing prediction errors based on online data to evaluate uncertain learning performance, and adjusting a neural network weight adaptive updating law in combination with tracking errors; and designing a channel coupling coordination control law in combination with equivalent control, switching control and feedforward neural network estimation information, and applying the channel coupling coordination control law to a hypersonic aircraft reentry section model. According to the method, a coordination control law is designed by fully utilizing the coupling characteristics of the aircraft, and neural network learning is performed by utilizing online data, sothat the problem of a large sideslip angle caused by insufficient yaw channels is solved, efficient coupling utilization of the aircraft is achieved, high-precision attitude control is obtained, anda new technical approach is provided for aircraft control.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to an aircraft channel coupling coordination control method based on data analysis, and belongs to the field of flight control. Background technique [0002] The structural shape and configuration of the aircraft ensure its excellent performance, but it also leads to serious control coupling. The common aircraft coupled attitude control research mainly considers the compensation or decoupling of the coupling, but there is a lack of research on how to use the coupling in advance. However, even if the coupling brings great control difficulties, reasonable use of the coupling can also enhance the control ability and improve the control effect. The control capability of the yaw channel during the reentry process of the aircraft is weaker than that of the roll channel and the pitch channel, and when the yaw control capability is insufficient, a large sideslip angle will be generated, which w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌寿莹鑫马波
Owner NORTHWESTERN POLYTECHNICAL UNIV
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