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Amplitude-phase comprehensive correlation identification method for helicopter spindle bending moment identification

A technology for helicopters and helicopter rotors, which is applied in the field of amplitude-phase comprehensive correlation recognition of helicopter main shaft bending moment marks, can solve problems such as difficulty in checking efficiency and validity test data, and achieve accurate and intelligent recognition.

Active Publication Date: 2022-02-25
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

Once the flight test is started, the limitations of these methods in terms of efficiency and effectiveness bring difficulties and challenges to test data verification

Method used

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  • Amplitude-phase comprehensive correlation identification method for helicopter spindle bending moment identification
  • Amplitude-phase comprehensive correlation identification method for helicopter spindle bending moment identification
  • Amplitude-phase comprehensive correlation identification method for helicopter spindle bending moment identification

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Embodiment Construction

[0026] The present invention proposes a spindle bending moment identification method based on the multi-order harmonic amplitude-phase comprehensive correlation of large sub-samples, which is applied to the identification of the authenticity of the helicopter spindle bending moment measurement mark to ensure the validity and accuracy of the spindle bending moment measurement data. The accuracy of the method is verified by using the actual flight measurement data of the main propeller shaft bending moment of a certain type of helicopter. This method provides an efficient and reliable new method and new option for identifying the authenticity of the spindle bending moment measurement mark, which can solve the limitations of existing identification methods and improve the recognition accuracy of the spindle bending moment measurement mark. This method can be extended and applied to the intelligent identification of the authenticity of the identification of the measurement channel ...

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Abstract

The invention provides an amplitude-phase comprehensive correlation identification method for helicopter spindle bending moment identification. The method comprises the following steps: measuring rotor wing main shaft section bending moment original data of a helicopter, and carrying out harmonic analysis on the rotor wing main shaft section bending moment original data to obtain an amplitude sequence and a phase sequence; respectively calculating the Pearson product-moment correlation coefficient of the amplitude sequence of the first-order harmonic component of any two test channels and the Pearson product-moment correlation coefficient of the phase sequence of the first-order harmonic component of any two test channels; respectively carrying out arithmetic mean value calculation on the Pearson product-moment correlation coefficient of the amplitude sequence and the Pearson product-moment correlation coefficient of the phase sequence to obtain an amplitude correlation coefficient arithmetic mean value and a phase correlation coefficient arithmetic mean value; multiplying the amplitude correlation coefficient arithmetic mean value by the phase correlation coefficient arithmetic mean value to obtain an amplitude-phase comprehensive correlation coefficient rFpsi of the two test channels; and judging whether the bending moment identifiers of the two test channels are accurate or not according to the amplitude-phase comprehensive correlation coefficient rFpsi.

Description

technical field [0001] The invention is used in the field of helicopter test data analysis, and in particular relates to an amplitude-phase comprehensive correlation identification method of a helicopter main shaft bending moment mark. Background technique [0002] With the development of modern test sensor performance, test methods and inspection technology, it has been able to accurately measure the required main shaft bending moment, obtain the load on the main shaft of the helicopter rotor and the heading force, lateral force, pitching bending moment and Rolling moment is used for real-time monitoring and evaluation of the spindle load threshold, spindle service life evaluation, flight safety control, etc. At the same time, due to the large number of measuring endpoints of the spindle bending moment, it is easy to cause misidentification. If the measurement identification error occurs, it will mislead the analysis of the result data and characteristics and the subsequen...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01L5/00
CPCG01L5/0061Y02T90/00
Inventor 黄斌根王文涛查建平李明强范学伟刘忠超陈浩
Owner CHINA HELICOPTER RES & DEV INST
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