热力耦合作用下复合材料搭接结构强度研究

余芬; 刘武帅; 王伟韬; 何振鹏

doi:10.13433/j.cnki.1003-8728.20180241

热力耦合作用下复合材料搭接结构强度研究

doi: 10.13433/j.cnki.1003-8728.20180241

中国民航大学航空工程学院, 天津 300300

基金项目:

中央高校基本科研基金项目 3122015C015

国家自然科学基金项目 51505482

中国民航局科技计划项目 MHRD20160106

详细信息

作者简介:
余芬(1963-), 教授, 硕士, 研究方向为航空复合材料制造与修理, fyu@cauc.edu.cn

通讯作者:
何振鹏, 讲师, hezhenpeng@tju.edu.cn

中图分类号: V257
计量
- 文章访问数: 310
- HTML全文浏览量: 213
- PDF下载量: 22
- 被引次数: 0
出版历程
- 收稿日期: 2018-06-03
- 刊出日期: 2019-05-05

Study on Strength of Composite Lap Structures under Thermal Mechanical Coupling

Aeronautical Engineering Institute, Civil Aviation University of China, Tianjin 300300, China

摘要

摘要: 复合材料铆钉搭接结构在温度变化情况下强度的研究对复合材料在航空领域上的应用具有重要的意义。为研究温度的变化对复合材料铆钉搭接结构强度的影响，考虑到模型具有高度的非线性问题，因此选用ABAQUS/Explicit求解器进行热力耦合过程的准静态模拟。通过编写VUMAT子程序，修改了材料的本构模型，考虑了温度对复合材料基本属性的影响，添加了混合失效准则以及材料失效后的参数退化方式。在25℃和105℃条件下分别对有开孔的复合材料板进行了压缩的模拟和复合材料铆钉搭接结构进行了拉伸的模拟。研究结果表明，温度的升高会降低压缩载荷作用下复合材料板和拉伸载荷作用下复合材料铆钉搭接结构的刚度与强度。
- 复合材料铆钉搭接结构 /
- 热力耦合 /
- VUMAT子程序 /
- 强度
Abstract: The research on the strength of composite rivet lap structure under the temperature change is of great significance to the application of composite materials in aviation industry. In order to study the influence of the temperature change on the strength of the rivet overlapping structure, the ABAQUS/Explicit solver is selected to simulate the thermal mechanical coupling process. By writing the VUMAT subprogram, the constitutive model is modified. The effect of the temperature on the basic properties of the composite is taken into account, and the mixed failure criterion and the method of parameter degradation after the failure of the material are added. Under the temperatures of 25℃ and 105℃, the compression simulation of the composite plate with open holes and the tensile simulation of the composite lap structures are carried out. The results show that the increase in temperature will reduce the stiffness and strength of composite plate under the compression load and the stiffness and strength of composite lap structures under the tensile load.
- composite material rivet lap structure /
- thermal mechanical coupling /
- VUMAT subroutine /
- strength

HTML全文

图 1 复合材料铺层角度示意图

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图 2 VUMAT子程序计算流程图

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图 3 复合材料铆钉单搭接模型

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图 4 有限元模型

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图 5 受压缩载荷的复合材料板位移-载荷曲线

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图 6 受拉伸载荷的铆钉搭接结构位移-载荷曲线

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图 7 基体拉伸失效起始及扩展

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图 8 纤维压缩失效和基体压缩失效模式

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图 9 25 ℃和105 ℃条件下搭接结构动能与内能比值

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表 1 刚度退化模式

损伤类型	材料参数退化方式
基体拉伸	E₂₂=0.2E₂₂, G₁₂=0.2G₁₂, G₂₃=0.2G₂₃
基体压缩	E₂₂=0.4E₂₂, G₁₂=0.4G₁₂, G₂₃=0.4G₂₃
纤维拉伸	E_ii=0.07E_ii, G_ij=0.07G_ij, υ_ij=0.07υ_ij(i, j=1, 2, 3, i≠j)
纤维压缩	E_ii=0.14E_ii, G_ij=0.14G_ij, υ_ij=0.14υ_ij(i, j=1, 2, 3, i≠j)
纤维基体剪切	G₁₂=0.1G₁₂, υ₁₂=0.1υ₁₂
分层	E₃₃=0.1E₃₃, G₂₃=0.1G₂₃, G₁₃=0.1G₁₃, υ₂₃=0.1υ₂₃, υ₁₃=0.1υ₁₃

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表 2 复合材料基本属性及性能指标(υ为无量纲值)

基本属性	数值/MPa	性能指标	数值/MPa
E₁	115 142	X_t	1 447
E₂	6 894	X_c	1 172
G₁₂	12 410	Y_t	68.9
υ	0.332	Y_c	262
		S	279

下载: 导出CSV

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