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A helicopter tail rotor support bearing fatigue test device

A technology for helicopter tail rotor and support bearing, which is used in mechanical bearing testing and other directions

Active Publication Date: 2017-06-23
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, my country's tail rotor support bearing fatigue test device can only perform variable pitch angular motion

Method used

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  • A helicopter tail rotor support bearing fatigue test device
  • A helicopter tail rotor support bearing fatigue test device
  • A helicopter tail rotor support bearing fatigue test device

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Embodiment Construction

[0018] Below in conjunction with accompanying drawing, this patent is described in further detail.

[0019] A fatigue test device for a helicopter tail rotor support bearing, comprising a bearing support 1, an outer frame 2, a support bearing connecting bolt 3, a support bearing 4, a support bearing pad 5, a flexible beam dummy 6, and a peelable gasket 7 , Rolling bearing support bolt 8, bearing retaining ring 9, rolling bearing 10, bottom plate 11;

[0020] Bearing support 1 is a single-ear bearing support, with fixed connection holes on both sides of the bottom of the support, bearing installation holes, bearing stop shoulders and bearing retaining ring grooves on the bearing support, see figure 1 . The middle of the outer frame 2 is a rectangular frame structure. There is a rotating shaft at both ends of the rectangular frame and the axis of the rotating shaft is on the intersection line of the symmetrical planes of the rectangular frame. There are shoulders on the rotatin...

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Abstract

A helicopter tail rotor support bearing fatigue test device, which belongs to the helicopter tail rotor support bearing fatigue test technology, is characterized in that the bearing support is a single-ear bearing support; the support bearing pad is a square structure as a whole, with a groove in the middle , the middle of the flexible beam dummy is a square platform, and the two ends are rotating shafts; the supporting bearing pads are bonded to the square platform of the beam dummy, and the supporting bearings are compressed with compression bolts and installed on the supporting bearing pads. The outer frame passes through two The first rolling bearing assembly is fixed on the bottom plate, and the outer frame and the supporting bearing are connected and tightened by the supporting bearing connecting bolts. The rolling bearing assembly is installed at both ends of the flexible beam dummy and the rolling bearing support bolts are fixed to ensure that the rotation axis of the outer frame rotates with the flexible beam dummy. The axes are perpendicular to each other and in the same plane. The invention realizes the synchronous high-frequency loading of the swing angle and the variable pitch angle, truly simulates the working environment of the tail rotor support bearing in the flight state of the aircraft, and achieves the purpose of evaluating the fatigue performance of the tail rotor support bearing.

Description

technical field [0001] The invention belongs to the fatigue test technology of a helicopter tail rotor support bearing, and relates to the design of a fatigue test device for a helicopter tail rotor support bearing. Background technique [0002] The tail rotor support bearing is an important part of the tail rotor blade, and it must bear the swing angular displacement from the flexible beam and the pitch angular displacement transmitted to it by the outer frame of the tail rotor blade sleeve. In order to grasp the fatigue performance of the tail rotor support bearing, it is necessary to conduct a fatigue test on the tail rotor support bearing on the ground to grasp the fatigue characteristics of the tail rotor support bearing, and then give the life of the tail rotor support bearing. At present, the fatigue test device of the tail rotor support bearing in my country can only carry out the angular motion of variable pitch. Contents of the invention [0003] The purpose of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/04
Inventor 孙云伟帅剑华罗伟
Owner CHINA HELICOPTER RES & DEV INST
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