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Adaptive fault diagnosis method of aircraft generator rectifier

A fault diagnosis, rectifier technology, applied in the direction of instruments, measuring electricity, measuring electrical variables, etc., can solve the problems of insulation layer damage, diode reverse breakdown, diode open circuit, etc.

Active Publication Date: 2015-05-20
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The failure of the aircraft generator rectifier is mainly due to the failure of the diode, the reverse breakdown of the diode or the destruction of the insulation layer, etc., which will eventually cause the diode to open circuit

Method used

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  • Adaptive fault diagnosis method of aircraft generator rectifier
  • Adaptive fault diagnosis method of aircraft generator rectifier
  • Adaptive fault diagnosis method of aircraft generator rectifier

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Embodiment Construction

[0042] Describe the present invention below in conjunction with specific embodiment:

[0043] The present invention belongs to a method of health monitoring and prediction, the core of the method is to realize offline and online health monitoring, with attached figure 2 The solid line and the dotted line are used to distinguish, the implementation represents the offline process, and the dotted line represents the online monitoring process. The present invention learns multiple classifiers by adjusting the weights of training samples, and linearly combines these classifiers. Compared with other machine learning methods, the present invention can adjust the weight of the classifier results, and the classifier with good classification effect is assigned a large weight, and the classifier with poor classification effect is assigned a small weight, thereby adaptively improving fault classification accuracy. At the same time, this method adaptively selects the fault features, ass...

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Abstract

The invention provides an adaptive fault diagnosis method of an aircraft generator rectifier. State monitoring and fault detection of the aircraft generator rectifier are realized. The implementation contents of the method comprise the following steps: determining working modes of a diode of the aircraft generator rectifier; acquiring historical data of the diode of the aircraft generator rectifier under various working modes; training by using the historical data; establishing classifiers for various working modes of the diode of the aircraft generator rectifier on the basis of a stumps method; changing weights of the different classifiers by using an adaptive method to generate an integral binary classifier; finally introducing an active learning mechanism by using a Generalized Bradley-Terry model to form a multi-classifier. The method is integrated in FADEC (Full Authority Digital Engine Control) of an aircraft engine, so fault monitoring of the generator rectifier can be realized, the accuracy and the efficiency for fault diagnosis of the aircraft generator rectifier are improved, and connection can be automatically cut off by the system when a fault of the rectifier occurs to prevent damage from being caused to subordinate equipment.

Description

technical field [0001] The invention relates to a fault diagnosis method in the field of fault diagnosis, in particular to an adaptive fault diagnosis method for an aircraft generator rectifier. Background technique [0002] Aircraft operate in complex environments, which have high requirements for system reliability. The status monitoring, diagnosis and prediction of aircraft systems are important means to ensure aircraft safety. For example, aircraft systems need to monitor engine performance (such as patent: CN 1O3 370667 A), landing gear status (such as patent: CN 103963986), elevator control (such as Patent: CN 202987498) and various electronic and electromechanical equipment (such as patent: CN 102700718 A) are working normally and the status of each system of the aircraft. The overall state of these systems is affected by the lower subsystems, for example, anti-skid brake control box (such as patent: CN 104049630 A), aircraft cables (such as patent: 103558513 A) and ...

Claims

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Application Information

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IPC IPC(8): G01R31/00
Inventor 刘贞报樊大森张超布树辉
Owner NORTHWESTERN POLYTECHNICAL UNIV
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