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Anti-twist device for rotor hub attachment fatigue test

A technology of fatigue test and rotor hub, which is applied in the direction of measuring device, testing of mechanical components, testing of machine/structural components, etc. It can solve the problem of affecting the monitoring of test status, the noise of the test environment, and the inability to apply the force of variable pitch rods, etc. problems, to achieve the effects of improved test efficiency, stable test bench, and small load fluctuations

Inactive Publication Date: 2016-06-29
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

[0003] The fatigue test of the main propeller hub connector assembly adopts the "resonance method" of mechanical excitation loading of the motor at the end of a cantilever beam hinged at one end. The application of the tension rod force cannot be realized, and the engineering method is used in the life analysis. The influence of the tie rod force on the main propeller hub connector group, and the test environment is noisy, which affects the monitoring of the test status

Method used

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  • Anti-twist device for rotor hub attachment fatigue test
  • Anti-twist device for rotor hub attachment fatigue test

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Embodiment Construction

[0017] The present invention will be described in further detail below.

[0018] Such as figure 1 , figure 2 As shown, the present invention is an anti-twist device for a fatigue test of a rotor hub connector, comprising: a fixed support 1, two shank joint bearing assemblies 2, a force measuring rod 3, a left threaded screw joint 4, an adjustment sleeve Pipe assembly 5, right threaded screw joint 6, connecting support 7, compression plate 8, pressure beam 9, simulated paddle root joint 10; fixed end of fixed support 1 is fixedly connected with test bench, fixed support 1 The other end is fixedly connected to one end of a shank joint bearing assembly 2, and one end of the force measuring rod 3 is connected to the other end of the shank joint bearing assembly 2; the other end of the force measuring rod 3 is connected to one end of the left threaded screw joint 4; The other end of the left threaded screw joint 4 is connected to one end of the adjustment sleeve assembly 5; the ...

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Abstract

The invention belongs to the rotor hub attachment fatigue testing technology, and relates to an anti-twist device for a helicopter rotor hub attachment fatigue test. A main hub assembly is a typical complex key part in a helicopter structure. Loads from a blade, which include the centrifugal force, wielding bending moment and shimmy bending moment, are transferred to a central member through the attachment assembly. The attachment assembly also balances a damper force and a bending moment pull rod force. Since the structure has a complex shape, bears severe loads and meanwhile requires a minimized weight, the offering of an accurate fatigue test assessment environment and the acquisition of the real fatigue performance and weak points through the test assessment are essential to provide the basis for determining the service life of the device.

Description

technical field [0001] The invention belongs to the fatigue test technology of the rotor hub connector, and relates to an anti-twist device for the fatigue test of the helicopter rotor hub connector. Background technique [0002] The main hub connector assembly is a typical complex key component in the helicopter structure. The loads transmitted by the blades, including centrifugal force, flapping moment, and shimmy bending moment, are transmitted to the central part through the connector assembly. Balance damper force and pitch rod force. Due to the complex shape of the structure, the severe load it bears, and the lightest possible weight, it is very important to provide an accurate fatigue test assessment environment and conduct test assessment to obtain the real fatigue performance and weak parts to provide a basis for determining its service life. [0003] The fatigue test of the main propeller hub connector assembly adopts the "resonance method" of mechanical excitatio...

Claims

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Application Information

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IPC IPC(8): G01M13/00
Inventor 李清蓉喻溅鉴刘红艳李艳艳
Owner CHINA HELICOPTER RES & DEV INST
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