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A Method for Evaluating the Validity of Vibration Monitoring Data of Helicopter Moving Parts

A technology for data validity and vibration monitoring, applied in the field of data processing, to achieve the effect of improving validity and versatility

Active Publication Date: 2021-09-28
北京安达维尔航空设备有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for evaluating the validity of vibration monitoring data of helicopter moving parts, so as to solve the aforementioned problems existing in the prior art

Method used

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  • A Method for Evaluating the Validity of Vibration Monitoring Data of Helicopter Moving Parts
  • A Method for Evaluating the Validity of Vibration Monitoring Data of Helicopter Moving Parts
  • A Method for Evaluating the Validity of Vibration Monitoring Data of Helicopter Moving Parts

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Embodiment

[0039] The method for evaluating the validity of vibration monitoring data of helicopter moving parts described in this embodiment, the specific steps are as follows:

[0040] S1, read the data of the vibration acceleration signal of a measuring point collected by the monitoring equipment, extract the time domain and frequency domain characteristic values ​​in the vibration acceleration data of the measuring point through signal processing; detect the steady state of the engine The speed effective value Eng_CI_Vrms of the gas generator and the power turbine and the frequency division characteristic values ​​Eng_CI_1st_AMP and Eng_CI_2st_AMP;

[0041] The speed effective value Eng_CI_Vrms is the root mean square value of the vibration speed signal, the Eng_CI_1st_AMP is the first-order frequency amplitude with the same frequency as the engine shaft, and the Eng_CI_2st_AMP is the second-order frequency amplitude with the same frequency as the engine shaft.

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Abstract

A method for evaluating the validity of vibration monitoring data of helicopter moving parts. By extracting the eigenvalues ​​of the vibration acceleration signals collected by the monitoring system of the existing helicopter, and performing a series of data monitoring on the eigenvalues, the effective The vibration acceleration signal is screened through the validity data, and finally the effective vibration monitoring data is selected, and the fault is judged according to this; the evaluation method of the present invention is embedded in the airborne data of the helicopter usage monitoring system During the collection, the validity of the collected data can be improved, and it can be applied to the evaluation of the validity of the vibration acceleration data of different measuring points, with strong versatility; it can provide reliable data for the fault diagnosis and fault prediction algorithms of helicopter moving parts, and improve fault diagnosis and fault prediction. reliability of accuracy.

Description

technical field [0001] The invention relates to the field of data processing, in particular to a method for evaluating the validity of vibration monitoring data of helicopter moving parts. Background technique [0002] The three major moving parts of the helicopter include the engine, the rotor system and the transmission system, which are important components that affect the flight safety of the helicopter; during the take-off, landing and flight of the helicopter, the power of the engine changes greatly, the structure of the transmission system is complex, and the vibration caused by the rotor and tail rotor If it is large, it will cause damage to the power system and transmission system to a certain extent. At present, domestic research institutions have proposed the concept of condition-based maintenance, that is, to install online detection equipment on the helicopter, detect and locate faults as soon as possible, and use vibration acceleration signals as the data sourc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60G01H1/00G01H1/12G01H1/14G06F16/2455
CPCB64F5/60G01H1/003G01H1/12G01H1/14G06F16/24564
Inventor 张志雄郭占强夏春翔朱向伟王文涛王帅
Owner 北京安达维尔航空设备有限公司