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Complex braided structure ceramic matrix composite fatigue retardation behavior prediction method

A composite material and prediction method technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problem of inability to accurately predict the fatigue and hysteresis behavior of complex braided structures

Inactive Publication Date: 2016-06-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] Aiming at the deficiencies of the above prior art, the purpose of the present invention is to provide a method for predicting the fatigue hysteresis behavior of ceramic matrix composites with complex braided structures, so as to solve the problem in the prior art that the fatigue hysteresis behavior of complex braided structures cannot be accurately predicted. question

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  • Complex braided structure ceramic matrix composite fatigue retardation behavior prediction method
  • Complex braided structure ceramic matrix composite fatigue retardation behavior prediction method
  • Complex braided structure ceramic matrix composite fatigue retardation behavior prediction method

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Embodiment

[0100] The present invention takes the 2.5D-C / SiC composite material as an example, and simulates the fatigue hysteresis loops when the shallow cross-bending 2.5D-C / SiC composite material has fatigue failure and no fatigue failure at room temperature. Table 1 shows the basic material properties of fiber bundles at room temperature.

[0101] Table 1 Basic properties of C / SiC fiber bundle materials at room temperature

[0102]

[0103] (1) Based on the finite element method, a 2.5-dimensional unit cell model is established. According to the periodic characteristics, the structural size of the selected unit cell model is as follows: figure 1 shown. The unit cell model has a total of 5 parameters. Js is the warp span; Jh is the warp height; Jw is the warp width; Ww is the weft width; Wh is the weft height, and the size parameters are measured by photomicrographs. Through ANSYS commercial software, a 2.5-dimensional braided C / SiC composite mesostructure model was obtained, a...

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Abstract

The invention discloses a complex braided structure ceramic matrix composite fatigue retardation behavior prediction method. The method comprises the steps of calculating a fatigue stress-strain curve under circulation with a microscale model to obtain the unit constitutive relation, substituting the unit constitutive relation into a unit cell model to conduct corresponding stiffness reduction on the unit cell model under different boundary conditions, and conducting statistics on the average stress and average strain of the unit cell model to obtain a unit cell scale fatigue retardation loop under the cycle number. By means of the multiscale model, the micro stress-strain field of a complex braided structure can be given, and therefore the fatigue retardation behavior of the material can be predicted precisely.

Description

technical field [0001] The invention relates to a method for predicting the fatigue hysteresis behavior of ceramic matrix composite materials with a complex braided structure based on a multi-scale model. Background technique [0002] Complex braided ceramic matrix composites have excellent properties such as high specific strength, high specific modulus, high temperature resistance, corrosion resistance and low density, and have a wide range of demands in aerospace vehicle high temperature protection systems. During the use of materials, due to the influence of factors such as load and environment, component damage and even destruction will gradually occur. One of the main forms of damage is fatigue damage. Under the action of fatigue load, the stress-strain curve of the material will appear a hysteresis loop. The understanding of hysteresis loops is key to simulating and predicting material fatigue damage. Therefore, it is of great significance to study the fatigue hyste...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23G06F2119/04
Inventor 孙志刚陈西辉宋迎东杨福树
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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