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All-channel active disturbance rejection control method for aircraft maneuvering at high speed

An active disturbance rejection control and aircraft technology, which is applied in non-electric variable control, three-dimensional position/course control, vehicle position/route/altitude control, etc. Normal overload rate of change and other issues, to achieve the consistency of dynamic response and control accuracy, and reduce the effect of dependence

Active Publication Date: 2022-02-18
ACAD OF MATHEMATICS & SYSTEMS SCIENCE - CHINESE ACAD OF SCI
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AI Technical Summary

Problems solved by technology

[0003] 1. The dynamic inverse design requires an aerodynamic parameter model, and the uncertainty considered in the existing anti-disturbance method is mainly the external disturbance of the system, etc.;
[0004] 2. In the control design, the rate of change of normal overload is not estimated, and the proportional-differential feedback control of normal overload is not adopted.
[0005] Therefore, it is difficult to ensure the accuracy of overload control and flight stability when the aerodynamic characteristics change rapidly during high-speed maneuvers

Method used

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  • All-channel active disturbance rejection control method for aircraft maneuvering at high speed
  • All-channel active disturbance rejection control method for aircraft maneuvering at high speed
  • All-channel active disturbance rejection control method for aircraft maneuvering at high speed

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Embodiment Construction

[0087] Control block diagram see figure 1 , the controller design flow chart see figure 2 .

[0088] In order to test the practicability of the method of the present invention, a simulation experiment is carried out by taking a typical thrust vectoring aircraft high-speed maneuvering as an example.

[0089] Simulation conditions:

[0090] The flight altitude of the aircraft is 1500 meters, and the flight speed is 300 meters per second. The normal overload command is:

[0091]

[0092] Specific implementation steps:

[0093] 1. Set the initial value of ESO(2)-(4) as follows:

[0094]

[0095] And the bandwidth of ESO(2)-(4) is designed as:

[0096] ω nZ =15; ω β =15; ω p =15,

[0097] Thus calculating the output of ESO(2)-(4)

[0098] 2. Substitute the output of ESO(2)-(4) into formula (5) to calculate the virtual control quantity with disturbance compensation feedback control, namely

[0099]

[0100] where the parameters are taken as

[0101] k β = 1...

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Abstract

The present invention proposes a full-channel ADR control method for aircraft high-speed maneuvering, including the following four steps: 1. Establishing a high-speed maneuvering aircraft dynamics model oriented to ADRC; 2. Designing an expanded state observer to estimate the total disturbance and 3. Design the virtual control quantity of high-speed maneuvering control that compensates the total disturbance online; 4. Design the control allocation scheme. This method can realize the online estimation and compensation of the nonlinear uncertain dynamics of each channel, the coupling uncertain dynamics and external disturbances, and realize the expected dynamic performance of the closed-loop system, ensuring good dynamic quality in the high maneuvering control of the aircraft.

Description

technical field [0001] The invention belongs to the field of control design methods of aircraft, and relates to a control method for high-speed maneuvering of aircraft and a decoupling control design method with nonlinear uncertainty of aerodynamic parameters and multi-channel coupling uncertainty. This technology is an effective solution to realize the overload control in the high-speed maneuvering of the aircraft by using the active disturbance rejection control method, and to ensure the stability of the heading channel and the lateral channel. Background technique [0002] High-speed maneuvering is one of the necessary capabilities of high-performance aircraft. Large overload control during high-speed maneuvering often faces strong nonlinear uncertainties in aerodynamic parameters and multi-channel coupling. Therefore, how to realize the precise control of large overload during high-speed maneuvering and ensure the stability of each channel under multi-channel coupling is...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/101
Inventor 黄一薛文超陈森
Owner ACAD OF MATHEMATICS & SYSTEMS SCIENCE - CHINESE ACAD OF SCI
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