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Test method for obtaining propeller hub bending moment of helicopter under non-rotating coordinate system

A helicopter, non-rotating technique used in the application of a stable bending force to test the strength of materials, measuring devices, instruments, etc.

Active Publication Date: 2022-03-15
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a test method for obtaining the bending moment of the propeller hub in the non-rotating coordinate system of the helicopter, and solves the engineering problem of the bending moment test of the propeller hub in the coordinate system of the aircraft body

Method used

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  • Test method for obtaining propeller hub bending moment of helicopter under non-rotating coordinate system
  • Test method for obtaining propeller hub bending moment of helicopter under non-rotating coordinate system
  • Test method for obtaining propeller hub bending moment of helicopter under non-rotating coordinate system

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Embodiment 1

[0041] The technical solution of the present invention is: a test method for obtaining the bending moment of the rotor hub in the non-rotating coordinate system of the helicopter. load. The test steps are as follows:

[0042] Step 101: arrange two rotor shaft bending moment measurement points, and set bending moment measuring equipment on each rotor shaft bending moment measurement point;

[0043] Specifically, the location of the rotor shaft bending moment measurement point and the bending moment testing equipment are determined on the rotor shaft according to the structural features.

[0044] Step 102: Calibrate the bending moment testing equipment at the rotor shaft bending moment measuring point, and obtain the correlation between the rotor shaft bending moment of the section of the rotor shaft bending moment measuring point and the output data of the rotor shaft bending moment measuring point;

[0045] The method steps of calibrating the bending moment test equipment at...

Embodiment 2

[0076] In the following, the present invention will be further described in detail in conjunction with the embodiment of the hub bending moment test of a certain type of machine in a non-rotating coordinate system. A test technology for obtaining the bending moment of the helicopter hub in the non-rotating coordinate system, characterized in that, through the physical relationship between the azimuth signal receiver and the measuring point of the bending moment of the rotor shaft in the rotating coordinate system, the bending moment of the rotor shaft in the rotating coordinate system is The output data of the moment measurement point is decomposed and converted into the hub bending moment in the non-rotating coordinate system of the helicopter. The test steps are as follows:

[0077] [1] Arrange rotor shaft bending moment measurement points, and set bending moment measurement equipment at each rotor shaft bending moment measurement point

[0078] The rotor shaft is simplified...

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Abstract

The invention provides a testing method for acquiring a propeller hub bending moment of a helicopter under a non-rotating coordinate system. The method comprises the following steps: determining a mounting angle theta 1 of an azimuth signal transmitter and rotor shaft bending moment measuring equipment; determining an angle theta 2 between the azimuth signal receiver and the longitudinal center line of the helicopter body; calculating a phase difference (theta1 + theta2); extracting a first rotor shaft loading bending moment of the two rotor shaft bending moment measuring points when the azimuth angle signal receiver outputs the pulse signal, and a second rotor shaft loading bending moment before 1 / 4 pulse circulation; according to the phase difference (theta1 + theta2), the first rotor shaft loading bending moment and the second rotor shaft loading bending moment of each rotor shaft bending moment measuring point are decomposed, and the transverse bending moment and the longitudinal bending moment of the helicopter body corresponding to the rotor shaft bending moment measuring points are obtained; according to the positions of the two rotor shaft bending moment measuring points, the transverse bending moment and the longitudinal bending moment of the helicopter body at the two rotor shaft bending moment measuring points are converted into the propeller hub bending moment under the helicopter non-rotating coordinate system.

Description

technical field [0001] The invention belongs to the field of helicopter strength design and relates to a test method for obtaining the bending moment of a helicopter hub in a non-rotating coordinate system. Background technique [0002] The helicopter hub bending moment load is transmitted from the continuously rotating rotor shaft during flight to the helicopter body which is fixed relative to the rotor shaft. The propeller hub bending moment can be divided into the transverse bending moment and longitudinal bending moment of the airframe. Among them, the measurement technology of the propeller hub bending moment is relatively mature. However, it is difficult to directly measure the transverse bending moment and longitudinal bending moment of the airframe, which cannot meet the strength analysis requirements of the corresponding airframe structure. [0003] Helicopter hub bending moment measurement technology is relatively mature. Usually, test points are arranged on the ro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/20
CPCG01N3/20G01N2203/0023G01N2203/0676Y02T90/00
Inventor 吴艳霞孙思赵江周亚妮
Owner CHINA HELICOPTER RES & DEV INST