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Composite laminate II-type fatigue delamination test device suitable for high and low temperature environments

A technology of composite material layer, test device, applied in the direction of using applied stable tension/compression to test material strength, measuring device, analyzing material, etc.

Active Publication Date: 2020-09-04
CHONGQING UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, through the three-point bending test device, only the type II fatigue load under the condition of normal stress ratio can be applied

Method used

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  • Composite laminate II-type fatigue delamination test device suitable for high and low temperature environments
  • Composite laminate II-type fatigue delamination test device suitable for high and low temperature environments
  • Composite laminate II-type fatigue delamination test device suitable for high and low temperature environments

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Experimental program
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Effect test

Embodiment Construction

[0027] See attached figure 1 , the test device is installed on the MTS testing machine with bolts, and is used to carry out the type II fatigue delamination test of the composite material laminate under the condition of negative stress ratio.

[0028] as attached figure 1 , the position of the collet is determined through the positioning threaded hole to ensure that the device is coaxial with the position of the loading device of the MTS testing machine; the gland and the base clamp one end of the composite material specimen through screws; two pairs of perforated rectangular blocks and rollers All adopt clearance fit, and glue the upper and lower sides of the other end of the composite material specimen respectively; the chuck is connected with the MTS testing machine; the upper and lower rollers roll between the upper and lower contact surfaces of the chuck.

[0029] Generally, the internal space of high and low temperature environmental chambers is limited. By installing g...

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Abstract

The invention relates to a composite laminated plate II-type fatigue delamination test device suitable for high and low temperature environments. The device comprises a base, a gland, a rectangular hole, a pin roller and a chuck. According to the invention, clamping of a test piece can be realized, and II-type fatigue loading under the negative stress ratio condition is carried out on the test piece through a fatigue testing machine. Besides, the structural size of the test device can be flexibly adjusted in the length direction of the test piece, so that the requirement on the space size of the environment box is greatly reduced, and II-type fatigue delamination tests in different environments are facilitated. The method is suitable for the fields of aerospace engineering and the like, isused for researching the fatigue layering expansion rate and the damage mechanism of the composite laminated plate under the negative stress ratio condition in the high and low temperature environment, provides technical support and theoretical basis for aerospace structure damage tolerance design, and guarantees the integrity and the safety of the structure in the service process.

Description

technical field [0001] The invention relates to a type II fatigue delamination test device for composite material laminates suitable for high and low temperature environments, and is suitable for research on the fatigue fracture behavior and failure mechanism of composite material laminates widely used in aerospace and other fields. Background technique [0002] Carbon fiber reinforced composites have been widely used in the aerospace field due to their excellent mechanical properties such as specific strength and specific modulus. The laminated structure is a common application method of composite material components. Prepregs are laid according to the designed angle. Each layer of prepregs contains reinforcing fibers and a matrix. The matrix material of adjacent prepregs is finally cured to form a composite material component. The composite laminated structure lacks reinforcement in the thickness direction, so it is easy to delaminate and damage under out-of-plane loads, e...

Claims

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Application Information

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IPC IPC(8): G01N3/08G01N3/04
CPCG01N3/08G01N3/04G01N2203/0208G01N2203/0073G01N2203/0096
Inventor 龚愉张寒松姚建尧刘浩张建宇
Owner CHONGQING UNIV