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Fatigue test device for outer front flap and joint test piece

A fatigue test and test piece technology, applied in the field of aircraft structure fatigue test, to achieve the effect of saving test resources and compact structure

Active Publication Date: 2020-04-14
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of this application is to provide a fatigue test device for the outer front flap and joint test piece to solve or alleviate at least one of the problems in the background art

Method used

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  • Fatigue test device for outer front flap and joint test piece
  • Fatigue test device for outer front flap and joint test piece
  • Fatigue test device for outer front flap and joint test piece

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Embodiment Construction

[0033] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0034] Such as Figure 1 to Figure 5 As shown, in order to carry out the fatigue test of the outer front flap and the joint, the outer front flap and the joint test piece are constructed at first in the present application, and the said test piece is the same or similar to the real structure, and it is mainly composed of the front flap 51, the front joint 52 and the rear Connector 53 consists of, as figure 2 shown.

[0035] For this reason, the fatigue test device for the outer front flap and the joint test piece proposed by the application includes: test bench 1, pulley seat assembly support structure 2, actuator fixed beam 3, lever support support structure 4, test piece Support 6, front joint loading m...

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Abstract

The invention relates to a fatigue test device for an outer front flap and joint test piece. The device comprises: an integral test bench; a pulley seat assembly supporting structure, an actuator cylinder fixing cross beam and a lever support supporting structure which are fixed on the test bench; a test piece supporting structure which is fixed on the test bench; a front joint loading mechanism which can apply a load to the front joint through a front joint loading actuator cylinder and a lever; and a rear joint loading mechanism which can apply a lateral load to a rear joint through a lateral loading actuator cylinder, can apply a course load to the rear joint through a course loading actuator cylinder, and can convert the applied vertical load into the course load to the rear joint through a vertical loading actuator cylinder and a pulley. According to the invention, the fatigue test function and loading requirements of the outer front flap and the joint can be met, effective test piece boundary condition simulation is carried out, and the rigidity and strength requirements of the test are met.

Description

technical field [0001] The application belongs to the technical field of aircraft structure fatigue tests, and in particular relates to a fatigue test device for outer front flaps and joint test pieces. Background technique [0002] The outer front flap and its joint structure are widely used in the aircraft flap and slat structure, and the fatigue performance of the structure seriously affects the flight safety of the aircraft. This structural form has both the joint and the load-carrying characteristics of the wall plate. Due to the complex structure, small test piece, compact structure, and long test period, it is necessary to design a special device for fatigue test. For the fatigue test of the outer front flap and joint structure, there is no relevant report so far. The invention designs a fatigue test device for the outer front flap and joint test piece, which meets the function and loading requirements of the outer front flap and joint fatigue test. Contents of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60G01N3/08G01M13/00
CPCB64F5/60G01M13/00G01N3/08G01N2203/0258
Inventor 李耀庞宝才魏玉龙张文东孙汉斌
Owner CHINA AIRPLANT STRENGTH RES INST
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