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A clamping device that satisfies the stable installation of the cantilever shaft

A clamping device and cantilever shaft technology, applied in the field of aviation test, can solve the problem of inability to meet the stability and reliability of the middle main shaft hole, and achieve the effect of stable and reliable loading process, avoiding unsustainable loading, and reliable loading.

Active Publication Date: 2021-10-08
CHANGHE AIRCRAFT INDUSTRIES CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the current technology cannot meet the stable reliability of the installation at the middle spindle hole

Method used

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  • A clamping device that satisfies the stable installation of the cantilever shaft

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Embodiment Construction

[0012] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0013] Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practice...

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Abstract

The invention discloses a clamping device capable of satisfying the installation stability of a cantilever shaft. The device includes: a mounting plate, an upper nut, a cantilever shaft, a transition plate, a lower nut and a plurality of connecting shafts. Among them: the mounting plate fixes one end of the cantilever shaft through the upper nut; the other end of the cantilever shaft and the transition plate are fixed through the lower nut; the specimen is installed between the two ends of the cantilever shaft; the transition plate and the connecting shaft are fixed through the lower nut; With the cantilever shaft as the center, multiple connecting shafts are evenly distributed around the transition plate. Through the ingenious design of the transition plate and the connecting shaft, the transition plate and the connecting shaft are firmly installed on the mounting plate; through the split design of the connecting shaft, the device cleverly avoids the installation interference of the test piece and realizes the test piece. Secure installation. The reliable loading of the cantilever shaft can be realized under the test state, and the loading process is stable and reliable, so as to avoid the unsustainable loading when the life parts are tested.

Description

technical field [0001] The invention relates to the technical field of aeronautical testing, in particular to a clamping device capable of satisfying the installation stability of a cantilever shaft. Background technique [0002] In the fatigue test of structural parts of aviation products, many parts need to be subjected to fatigue test, and the process of fatigue test should be adapted to the normal use environment of structural parts on the aircraft as much as possible. This requires us to design a set of devices to simulate the structural parts under the test environment of the installed state of the flying parts. It is very necessary to design a clamping device that meets the stability of the cantilever shaft installation. [0003] The five-prong part of a certain type of aircraft belongs to the installation of the cantilever shaft structure on the aircraft. In the test state, in order to realize the test, it is necessary to design a set to simulate the force of each pa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 梅火林赵越王斌林娜应少军史丽红
Owner CHANGHE AIRCRAFT INDUSTRIES CORPORATION