二维编织C/SiC复合材料板疲劳损伤分析

陈天雄; 张铮; 王奇志; 林彗星

doi:10.13700/j.bh.1001-5965.2018.0194

二维编织C/SiC复合材料板疲劳损伤分析

doi: 10.13700/j.bh.1001-5965.2018.0194

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
陈天雄男, 硕士研究生。主要研究方向:损伤力学、复合材料力学

张铮男, 博士, 副教授, 硕士生导师。主要研究方向:损伤力学和复合材料结构分析

通讯作者:
张铮, E-mail: jordanzzhang@buaa.edu.cn

中图分类号: O346.5;V414.8;V414.3
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- 被引次数: 0
出版历程
- 收稿日期: 2018-04-09
- 录用日期: 2018-05-04
- 网络出版日期: 2019-01-20

Fatigue damage analysis of 2D braided C/SiC composite plate

School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

More Information

Corresponding author: ZHANG Zheng, E-mail: jordanzzhang@buaa.edu.cn

摘要

摘要:
为探索复合材料损伤的基本规律，首先，基于损伤力学，结合Tsai-Hill强度理论，提出了表征二维编织C/SiC复合材料损伤各向异性的损伤演化方程；然后，在商业有限元软件ANSYS环境中进行了二次开发，形成了考虑材料刚度随损伤折减的损伤模拟程序；其次，对二维编织C/SiC复合材料板模型进行了损伤模拟分析，结果表明材料损伤过程中应力与损伤度对单元破坏起共同作用；最后，对损伤演化方程的形式提出了讨论与改进，并通过模拟计算揭示了复合材料在损伤驱动力及材料特性作用下损伤呈现各向异性演化的特征，说明材料各向异性损伤是其材料特性及受载形式产生的必然结果。
- 复合材料 /
- 二维编织 /
- 损伤 /
- 各向异性 /
- 有限元
Abstract:
To explore the basic laws of composite damage, first, based on damage mechanics, combined with Tsai-Hill criterion of strength, a damage evolution equation that can characterize the damage anisotropy of 2D braided C/SiC composites was proposed.Second, a damage simulation program considered material stiffness reduction depend on the damage degree, as an add-on function, was developed and inserted in the commercial finite element software ANSYS environment. Third, the damage evolution of the 2D braided C/SiC composite plate model was simulated, and the result shows stress and damage degree have coupling effects on the element damage during the damage process. Finally, the form of damage evolution equation is discussed and improved, and the anisotropic characteristics of damage evolution under the material property and the action of damage driving force is revealed by analog computation, indicating that the material anisotropy damage is the inevitable result of its material properties and loaded form.
- composite /
- 2D braided /
- damage /
- anisotropy /
- finite element

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图 1 计算程序流程图

Figure 1. Flowchart of calculation program

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图 2 模型及约束条件

Figure 2. Model and constraint condition

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图 3 应力分布云图

Figure 3. Stress distribution contour

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图 4 正交各向异性板正反表面损坏单元数

Figure 4. Number of damaged units on front-side and back-side surface of orthotropic plate

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图 5 正交各向异性板正反表面损伤进程分离

Figure 5. Front-side and back-side surface damage evolution separation of orthotropic plate

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图 6 板背面单元和板正面单元损伤度

Figure 6. Damage degree of plate back-side units and plate front-side units

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图 7 板背面单元和板正面单元等效应力

Figure 7. Equivalent stress of plate back-side units and plate front-side units

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图 8 板正面单元和背面单元的损伤度对比

Figure 8. Comparison of damage degree between plate units of front-side and back-side

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图 9 板正面单元和背面单元的等效应力对比

Figure 9. Comparison of equivalent stress between plate units of front-side and back-side

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图 10 正交各向异性三层板损坏单元数

Figure 10. Number of damaged units of orthotropic three-layer plate model

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图 11 正方形板不同强度条件下损伤扩展云图

Figure 11. Damage extension contour of square plate under different strength conditions

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表 1 正交各向异性薄板模型材料参数^[17]

Table 1. Material parameters of orthotropic thin plate model^[17]

参数	数值
弹性模量E₁、E₂/GPa	187.06
弹性模量E₃/GPa	16.49
泊松比μ₁₂	0.175
泊松比μ₁₃、μ₂₃	0.492
剪切模量G₁₂/GPa	57.66
剪切模量G₁₃、G₂₃/GPa	27.51

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表 2 正交各向异性薄板中间层和表面层材料参数

Table 2. Material parameters of middle layer and surface layer in anisotropic thin plate

参数	中间层	表面层
弹性模量E₁、E₂/GPa	107.06	187.06
弹性模量E₃/GPa	9.43	16.49
泊松比μ₁₂	0.1	0.175
泊松比μ₁₃、μ₂₃	0.484 5	0.492
剪切模量G₁₂/GPa	52.75	57.66
剪切模量G₁₃、G₂₃/GPa	15.75	27.51

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