Crack performance measurement and optimization solution method for composite material glue joint structure

A composite material and bonding technology, applied in the field of aerospace materials and materials science, can solve problems such as incomplete material properties, poor precision, and difficulty in solving parameters, and achieve clear physical meaning, fast speed, and high calculation accuracy.

Active Publication Date: 2015-11-04
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

However, when the constitutive relation of the material is not known, or the form of the constitutive relation is known, but the form is too complex to perform conventional statistical calculations
The interfacial crack growth performance of composite bonded structures is such a problem. Its constitutive relationship is very complex, usually a nonlin...

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  • Crack performance measurement and optimization solution method for composite material glue joint structure
  • Crack performance measurement and optimization solution method for composite material glue joint structure
  • Crack performance measurement and optimization solution method for composite material glue joint structure

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Embodiment Construction

[0027] In order to better understand the crack performance measurement and optimization solution method of the composite material bonding structure according to the scheme of the present invention, a preferred embodiment of the crack performance measurement and optimization solution method of the composite material bonding structure of the present invention will be further elaborated below. .

[0028] The purpose of the present invention is achieved through the following technical solutions: a crack performance measurement and optimization solution method of a composite material adhesive structure comprises the following steps:

[0029] S1: Establish a crack propagation constitutive relation model;

[0030] S2: Model adjustment for parameter optimization algorithm;

[0031] S3: Design and carry out the interface crack growth test of composite bonded structure;

[0032] S4: Use test data to optimize and solve performance parameters.

[0033] Preferably, in S1, the ductile ma...

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Abstract

The invention relates to a crack performance measurement and optimization solution method for a composite material glue joint structure and belongs to the field of technical research in aeronautical material science. The method comprises the following steps: 1, establishing a crack propagation constructive relation model; 2, designing glue joint layer crack propagation tests by combining constructive relation forms; 3, reversely measuring glue joint layer crack propagation performance parameters by utilizing the multi-variable optimization method, and establishing a complete interface crack propagation mathematic model and analysis method. The crack performance measurement and optimization solution method for the composite material glue joint structure is high in calculation precision and speed, the established crack propagation constructive relation is simple and easy to use, the wide practical application value is achieved, and processes of damage start, material degradation, crack generation and crack propagation of bonding layer materials can be completely revealed.

Description

technical field [0001] The invention relates to the technical field of aerospace material science research, in particular to a crack performance measurement and optimization solution method of a composite material bonding structure. Background technique [0002] It is very difficult to extend the existing crack propagation performance of metal materials to the cracks of composite materials, because the deformation and damage state of polymer materials with glue structure are very different from those of metal materials under high stress conditions. Accompanied by problems such as temperature rise, passivation, and large deformation, the crack growth performance model of metallic materials cannot be directly used. At present, there are many researches on the crack propagation of composite bonded structures, and many constitutive models have been established. However, due to material characteristics, these models are very complex, usually nonlinear implicit models, with many ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 卜英格洪海明周丽君
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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