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Vibration test device and test method for airplane panel connecting piece

A technology for vibration testing and connecting parts, applied in the field of standard parts testing, can solve the problems of cumbersome vibration direction conversion, inability to simulate the actual working environment of constant force load, etc., and achieve the effects of great practical value, easy popularization and application, and high test efficiency.

Active Publication Date: 2020-04-10
CHINA AERO POLYTECH ESTAB
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the shortcomings of the existing aircraft panel connector vibration test device that cannot simulate the actual working condition environment of constant force load, and the vibration direction conversion is cumbersome, a compact structure, which can simulate the actual constant force working condition load and convenient vibration direction conversion is provided. Vibration test device for aircraft panel connectors

Method used

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  • Vibration test device and test method for airplane panel connecting piece
  • Vibration test device and test method for airplane panel connecting piece
  • Vibration test device and test method for airplane panel connecting piece

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Embodiment Construction

[0045] Hereinafter, embodiments of the present invention will be described with reference to the drawings.

[0046] Such as figure 1 , figure 2 ,and Figure 6 A vibration test device for aircraft panel connectors is shown, which includes a vibration table 1 , an adapter unit 2 , a panel unit 3 and a loading unit 4 .

[0047] Such as image 3The shown adapter unit 2 includes an adapter plate 5 , a first pressure plate 6 , a first sleeve 7 , a second pressure plate 8 , a second sleeve 9 , a third pressure plate 10 , a third sleeve 11 , and a fourth pressure plate 12 And the fourth sleeve 13, the first pressure plate 6 is fixed on the threaded hole on the adapter plate 5 by bolts and the first sleeve 7, and the second pressure plate 8 is fixed on the adapter plate 5 by bolts and the second sleeve 9 The third pressure plate 10 is fixed on the threaded hole on the adapter plate 5 through bolts and the third sleeve 11, and the fourth pressure plate 12 is fixed on the threaded h...

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Abstract

The invention provides a vibration test device for an airplane panel connecting piece. The device comprises a vibration table, a switching unit, a panel unit and a loading unit. The vibration table isfixed on the ground, one mounting side surface of the switching unit is fixedly connected with the table surface of the vibration table, the panel unit is fixed on the switching unit through a pressing plate, one end of the loading unit is fixed on the switching unit, and the other end of the loading unit is connected with the panel unit through a steel wire rope. The invention further provides avibration test method for the aircraft panel connecting piece. The device is high in test efficiency and more accurate in test, is suitable for related tests of vibration and impact of the sandwich connection structure in the fields of aerospace, mechanical industry and the like, is easy to popularize and apply, and has a relatively high practical value.

Description

technical field [0001] The invention relates to the technical field of standard component testing, in particular to a vibration testing device and testing method for aircraft panel connectors. Background technique [0002] Aircraft panels and covers are parts used to realize the connection of structural components, quick opening of internal structures and decoration on aircraft. Typical aircraft panels and covers are connected by bolts and nuts, quick-release locks and other connectors. Typical aircraft panel structures are composed of upper interlayers, lower interlayers, and aircraft panel or cover connectors. [0003] The vibration test is to simulate the object or model in the laboratory to assess the vibration resistance performance under actual working conditions. Through the vibration assessment of the aircraft panel or the connector assembly of the flap, it is possible to simulate the actual working condition of the assembly, that is, under the condition of constant...

Claims

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Application Information

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IPC IPC(8): G01M7/06
CPCG01M7/06
Inventor 郭浩然张宗华吴子龙张辉隋明丽
Owner CHINA AERO POLYTECH ESTAB
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