Multi-stage monitoring system of stretching and fracture state of carbon fiber structure and monitoring method thereof

A tensile fracture and monitoring system technology, applied in the direction of applying stable tension/pressure to test material strength, measuring devices, and analyzing materials, can solve problems such as unrealized carbon fiber structure monitoring, and achieve distributed measurement and resolution High, guaranteed reliability and durability

Inactive Publication Date: 2013-06-12
SOUTHEAST UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the above-mentioned applications have not realized the whole process monitoring of carbon fiber structure fracture

Method used

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  • Multi-stage monitoring system of stretching and fracture state of carbon fiber structure and monitoring method thereof
  • Multi-stage monitoring system of stretching and fracture state of carbon fiber structure and monitoring method thereof
  • Multi-stage monitoring system of stretching and fracture state of carbon fiber structure and monitoring method thereof

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Embodiment Construction

[0032] The present invention will be further described below in conjunction with the accompanying drawings.

[0033] like Figure 1-5 As shown, the stage-by-stage monitoring system of the tensile fracture state of the carbon fiber structure includes a computer 7, a fiber grating analyzer 1, a Y-type fiber coupler 2, a first coupler joint 31, a second coupler joint 32, a first sensor Optical fiber 41, second sensing optical fiber 42, FBG strain sensing probe 5 and FBG strain wave sensing probe 6; computer 7 is connected to fiber grating analyzer 1, and Y-type fiber coupler 2 includes a Y-type fiber coupler input end 8 and two Y-type fiber coupler output ports 9, the Y-type fiber coupler input port 8 is connected to the fiber grating analyzer 1; two Y-type fiber coupler output ports 9, one of the Y-type fiber coupler output ports 9 It is connected with the first coupler joint 31, the first sensing fiber 41, and the FBG strain sensing probe 5 in turn, and the output end 9 of the...

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Abstract

The invention discloses a multi-stage monitoring system of stretching and fracture state of a carbon fiber structure. The system is characterized in that the system comprises a computer, an optical fiber and grating analyzer, a Y-typed optical fiber coupler, a fiber Bragg grating (FBG) strain sensing probe, an FBG strain wave sensing probe, a first coupler joint, a first sensing optical fiber, a second coupler joint and a second sensing optical fiber. The computer is connected with the optical fiber and grating analyzer, the Y-typed optical fiber coupler comprises an input end of the Y-typed optical fiber coupler and two output ends of the Y-typed optical fiber coupler, the input end of the Y-typed optical fiber coupler is connected with the optical fiber and grating analyzer, one output end of the Y-typed optical fiber coupler is connected sequentially with the first coupler joint, the first sensing optical fiber and the FBG strain sensing probe, and the other output end of the Y-typed optical fiber coupler is connected sequentially with the second coupler joint, the second sensing optical fiber and the FBG strain wave sensing probe. The system achieves monitoring of the whole process of the fracture of the carbon fiber structure.

Description

technical field [0001] The invention relates to a stage-by-stage monitoring system and a monitoring method for the tensile fracture state of a carbon fiber structure. Background technique [0002] Based on the characteristics of light weight, high strength, and strong design flexibility, as a high-performance structure with strong durability and high reliability, carbon fiber structure has solved the technical difficulties that could not be overcome by single-performance materials in the past, and has become an important technology for aviation, The mainstream trend of continuous development in high-tech fields such as aerospace is widely used in aircraft vertical stabilizers, fuselages, wings and other structures. However, during the manufacturing and long-term service of such materials, structural damage in the form of internal breakpoints, cracks, and delamination may occur. If the corresponding maintenance measures are not discovered in time, the entire structure will be...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/08G01N3/06G01B11/16
Inventor 刘宏月韩晓林费庆国芮琴张大海
Owner SOUTHEAST UNIV
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