Loading test device for rigid main propeller hub connecting piece

A technology of loading test device and main propeller hub, which is applied in the testing of mechanical components, testing of machine/structural components, measuring devices, etc., which can solve the problems that rigid main propeller hub connectors cannot be used, shorten working time, and quickly The effect of adjustment

Active Publication Date: 2022-03-11
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

[0005] The purpose of the present invention is: the present invention provides a loading test device for rigid main propeller hub connectors, to solve the fatigue loading test device for existi

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  • Loading test device for rigid main propeller hub connecting piece
  • Loading test device for rigid main propeller hub connecting piece
  • Loading test device for rigid main propeller hub connecting piece

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Embodiment Construction

[0051] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined arbitrarily with each other.

[0052] It has been explained in the above-mentioned background technology that the existing fatigue loading test device for the main propeller-hub connector is mainly used for the fatigue life assessment of the third-generation rotor represented by the spherical flexible propeller-hub connector. For the newly developed rigid rotor The above-mentioned existing fatigue loading test device is not applicable.

[0053] However, in the fatigue test, it is necessary to simulate the real boundary conditions of the rigid main rotor hub connection during flight, and apply loads such as...

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Abstract

The invention provides a loading test device for a rigid main propeller hub connecting piece. The loading test device comprises a propeller hub fake piece, a variable-pitch pull rod loading joint, a propeller blade fake piece, a steel cable, a propeller hub mounting bracket, a waving loading mechanism, a shimmy loading mechanism, a centrifugal force loading mechanism and a variable-pitch pull rod force loading mechanism. According to the fatigue test device and method for the rigid main propeller hub connecting piece, the blade false piece is designed, and the four loading actuators are adopted to apply test loads in four directions, so that the real boundary condition and the loaded state of the rigid main propeller hub connecting piece are simulated, and a real and accurate fatigue test assessment environment for the rigid main propeller hub connecting piece is provided; therefore, the fatigue dangerous part and the corresponding damage mode of the rigid main propeller hub connecting piece can be accurately determined, the fatigue characteristic of the rigid main propeller hub connecting piece is obtained, and an effective test basis is provided for the service life of the rigid main propeller hub connecting piece.

Description

technical field [0001] The present invention relates to but not limited to the technical field of fatigue testing of helicopter main rotor hub connectors, in particular to a loading test device for rigid main rotor hub connectors. Background technique [0002] In the past ten years, under the background of the rapid increase of comprehensive national strength, the research and development of helicopter models in my country has shown a blowout development, and new models supported by many new technologies have emerged. [0003] The main rotor hub connector is a typical complex moving part in the helicopter rotor system. The complex load transmitted from the blade is transmitted to the main rotor hub through the main rotor hub connector. The stress of the main rotor hub connector is very complicated. All the loads transmitted by the blades, fatigue damage is the main failure mode of the main rotor hub connector, and the fatigue performance of the main rotor hub connector direc...

Claims

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Application Information

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IPC IPC(8): G01M13/00G01N3/32G01N3/08B64F5/60
CPCG01M13/00G01N3/32G01N3/08B64F5/60G01N2203/0003G01N2203/0005G01N2203/0048G01N2203/0073Y02T90/00
Inventor 邓文钟翔福缪小飞
Owner CHINA HELICOPTER RES & DEV INST
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