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Multi-information fusion fault diagnosis method and system for thrust vectoring nozzle control system

A technology of multi-information fusion and control system, applied in the field of multi-information fusion fault diagnosis of vector nozzle control system, can solve problems such as low accuracy, improve accuracy, reduce feature dimension, reduce missed detection rate and false detection rate. The effect of the alarm rate

Active Publication Date: 2021-06-29
BEIHANG UNIV +1
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Problems solved by technology

[0005] The purpose of the present invention is to provide a multi-information fusion fault diagnosis method and system of a vector nozzle control system to solve the problem of low accuracy of the existing single sensor in the fault diagnosis process

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  • Multi-information fusion fault diagnosis method and system for thrust vectoring nozzle control system
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  • Multi-information fusion fault diagnosis method and system for thrust vectoring nozzle control system

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Embodiment approach

[0072] Based on the multi-information fusion fault diagnosis method of the vector nozzle control system provided by the present invention, as an optional embodiment of the present invention, the flow of the multi-information fusion fault diagnosis method based on D-S evidence theory is as follows:

[0073] Step 1: Obtain multi-source data information of the vector nozzle control system. Vector Nozzle A 91 The four failure modes of the actuating circuit are the diagnostic framework, that is, θ={F 1 , F 2 , F 3 , F 4}, representing system normality, servo valve wear, actuator wear and LVDT sensor drift, respectively. When a circuit of the vector nozzle device fails, it will affect the change of its own sensor signal, and at the same time, it will also affect the sensor signal in its coupling circuit, making other circuits appear certain fault characteristics. Therefore, the sensor signals with higher sensitivity to the fault state in the three loops of the vector nozzle con...

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Abstract

The invention relates to a multi-information fusion fault diagnosis method and system for a thrust vectoring nozzle control system. The method comprises the steps of acquiring multi-source data information in a working state of the thrust vectoring nozzle control system, and dividing the multi-source data information into a training set and a test set; performing wavelet denoising processing on the multi-source data information in a training set to determine a multi-source information data set; performing fault feature extraction on each kind of multi-source data information in the multi-source information data set, and determining a fault feature parameter data set of a multi-information domain; performing dimension reduction processing on the fault feature parameter data set by adopting a principal component analysis method, and determining a main metadata set; and based on the main metadata set, fusing the multiple pieces of single evidence body information by utilizing a D-S evidence theory, determining a probability distribution value for each fault state, and identifying a fault type according to a maximum probability criterion. According to the invention, the accuracy of fault diagnosis can be improved.

Description

technical field [0001] The invention relates to the field of fault diagnosis of an aero-engine control system, in particular to a multi-information fusion fault diagnosis method and system for a vector nozzle control system. Background technique [0002] As part of the aeroengine control system, the vector nozzle control system is composed of controllers, actuators, sensors and a large number of electronic components. It can not only provide sufficient thrust for fighter jets, but also cooperate with the aerodynamic force outside the Complete the function of yaw or reverse thrust, thereby greatly improving its own maneuverability and completing difficult movements. The axisymmetric vector nozzle can realize maneuvering deflection at any angle, and has the advantages of light structure, simple control principle, relatively mature technology and low risk. Moreover, the axisymmetric type has little change to the original structure of the engine, so the thrust vectoring technol...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0262G05B2219/24065
Inventor 石健张优优乔雅静王少萍
Owner BEIHANG UNIV
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