基于应变能耗散的复合材料层合板面内缺口强度分析CDM模型

吴义韬; 姚卫星; 吴富强; 沈浩杰

基于应变能耗散的复合材料层合板面内缺口强度分析CDM模型

1.
南京航空航天大学飞行器先进设计技术国防重点学科实验室, 南京 210016;
2.
南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016

基金项目: 国家自然科学基金（11202098）；教育部长江学者创新团队项目（IRT0968）；江苏高校优势学科建设工程资助项目

详细信息

通讯作者:
姚卫星，博士，教授，研究方向为飞行器综合设计和结构设计理论。E-mail：wxyao@nuaa.edu.cn

中图分类号: TB330.1;V258⁺.3
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出版历程
- 收稿日期: 2013-07-04
- 刊出日期: 2014-08-14

CDM model for analyzing intralaminar strength of notched composite laminates based on the dissipation of strain energy

1.
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2.
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 基于伴随能量释放的渐进损伤演化思想，建立了复合材料层合板面内失效分析的连续介质损伤力学（CDM）分析模型，该模型包含损伤表征、损伤起始判定和损伤演化法则3个方面。基于CDM模型，通过引入损伤状态变量表征损伤，建立了平面应力状态下的材料损伤本构模型。采用损伤参量 f_E改写Hashin准则，以判定损伤的起始。损伤演化由特征长度内的应变能释放密度控制，建立了损伤状态变量关于等效应变的渐进损伤演化法则。模型中还同时考虑了面内剪切非线性和网格敏感性，并进行了对比分析。对含缺口的[90/0/±45]_3s和[（±θ）₄]_s 2类典型复合材料层合板的面内拉伸失效进行了分析，结果表明，本文中的模型能有效预测复合材料层合板的面内拉伸强度。
- 复合材料 /
- 渐进损伤演化 /
- 拉伸强度 /
- 剪切非线性 /
- 网格敏感性
Abstract: Based on the viewpoint of progressive damage evolution with energy realease, a continuum damage mechanics (CDM) model, including damage description, damage initiation criterion and damage evolution law, was proposed for intralaminar failure analysis of composite laminates. Based on the CDM model, the damage constitutive of material in plane stress condition was established by introducing damage state variables which characterize corresponding damage. The damage initiation was estimated by using rewritten Hashin's criteria, which was expressed with damage parameter f_E. The damage evolution was controlled by the density of strain energy release within the characteristic length. The progressive damage evolution law associating damage state variables with equivalent strain was established. Intralaminar shear nonlinearity and mesh sensitivity were also taken into accounts in the model and analyzed comparatively. Failure analysis of notched[90/0/±45]_3s and[(±θ)₄]_s composite laminates under intralaminar tensile load was implemented, and the result shows that the present model is capable of predicting the intralaminar tensile strength of composite laminates.
- composites /
- progressive damage evolution /
- tensile strength /
- shear nonlinearity /
- mesh sensitivity