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Coordinated Control Method of Aircraft Channel Coupling Based on Data Analysis

A technology of coordinated control and aircraft, applied in the field of flight control, to improve learning accuracy and achieve efficient coupling and utilization

Active Publication Date: 2022-06-21
NORTHWESTERN POLYTECHNICAL UNIV +1
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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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  • Coordinated Control Method of Aircraft Channel Coupling Based on Data Analysis
  • Coordinated Control Method of Aircraft Channel Coupling Based on Data Analysis
  • Coordinated Control Method of Aircraft Channel Coupling Based on Data Analysis

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Embodiment Construction

[0052] The present invention will now be further described in conjunction with the embodiments and accompanying drawings:

[0053] refer to figure 1 , the present invention is a data analysis-based aircraft channel coupling coordination control method, which is realized by the following steps:

[0054] (a) Using the aircraft reentry 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 inclination 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 is the roll angular rate, ω y is the yaw rate, ω z is the pitch rate, M c =[M x ,M y ,M z ] T represents the control torque of the system, M x represents the rolling moment, M y represents the yaw moment, M z represents the pit...

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Abstract

The invention relates to a data analysis-based aircraft channel coupling coordination control method. The method is based on the dynamic model of the re-entry section of the aircraft, analyzes the characteristics of the model to define a three-layer sliding surface, and uses the Filippov equivalent theory to design an equivalent control law. Sliding mode control principle design switching control law; use neural network to estimate the unknown dynamics of the system, construct prediction error based on online data to evaluate uncertain learning performance, adjust neural network weight adaptive update law combined with tracking error; combine equivalent control and Switch control and feed-forward neural network estimation information, design channel coupling coordination control law, and apply to hypersonic vehicle re-entry model. The present invention makes full use of the coupling characteristics of the aircraft to design the coordination control law, and uses online data for neural network learning, which makes up for the large sideslip angle problem caused by the lack of yaw channels, realizes efficient coupling utilization of the aircraft and obtains high-precision control of the attitude, It provides a new technical approach for aircraft control.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to a data analysis-based aircraft channel coupling coordination control method, which belongs to the field of flight control. Background technique [0002] The structure, shape and configuration of the aircraft ensure its excellent performance, but also lead to serious manipulation coupling. Common aircraft coupled attitude control research mainly considers the compensation or decoupling of the coupling, but there is a lack of related research that considers how to use the coupling in advance. However, even if the coupling brings great control difficulties, rational use of the coupling can enhance the control ability and improve the control effect. Compared with the roll channel and pitch channel, the control ability of the yaw channel during the re-entry process of the aircraft is weaker, and when the yaw control ability is insufficient, a large sideslip angle will be generated, which ...

Claims

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Application Information

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