一种预测复合材料棘轮行为的循环塑性-损伤模型

成磊; 肖毅; 王杰; 薛元德

doi:10.13801/j.cnki.fhclxb.20210115.002

一种预测复合材料棘轮行为的循环塑性-损伤模型

doi: 10.13801/j.cnki.fhclxb.20210115.002

成磊^1,,
肖毅^1, ,,
王杰^2,,
薛元德^1,

1.
同济大学　航空航天与力学学院，上海 200092
2.
ABB电网投资(中国)有限公司，北京 100000

基金项目: 国家自然科学基金 (52078362)

详细信息

通讯作者:
肖毅，教授，博士生导师，研究方向为复合材料力学、结构强度分析与设计　 E-mail：y_xiao@tongji.edu.cn

中图分类号: TB330.1
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- 被引次数: 0
出版历程
- 收稿日期: 2020-11-13
- 录用日期: 2021-01-02
- 网络出版日期: 2021-01-15
- 刊出日期: 2021-10-01

A cyclic plasticity-damage model for predicting ratcheting behavior of composite materials

CHENG Lei^1
,,
XIAO Yi^{1
, ,},
WANG Jie^2
,,
XUE Yuande^1
,

1.
School of Aerospace Engineering and Applied Mechanics, Tongji University, Shanghai 200092, China
2.
ABB Power Grids Investment (China) Limited, Beijing 100000, China

摘要

摘要: 构建循环塑性本构模型并揭示其微观机制，目前仍然是复合材料力学研究富有挑战性的课题。本文提出了一种循环塑性-损伤模型，用以预测在循环载荷作用下纤维增强复合材料的应力-应变响应。该模型是在作者前期提出的描述非线性滞后行为的弹塑性本构模型的基础上的进一步扩展。它可以预测加载时的非线性响应、卸载和重加载时的迟滞行为及大量循环下的棘轮现象。作为基准问题验证，将Kawai等的实验数据与本文模型的数值预测进行了比较。结果表明，该模型能够模拟碳纤维/环氧树脂单向复合材料在偏轴循环加载下的棘轮行为。
- 纤维增强聚合物复合材料 /
- 循环塑性 /
- 迟滞行为 /
- 棘轮效应 /
- 疲劳损伤
Abstract: It is still a challenging problem to establish a constitutive model for cyclic plasticity and reveal its microscopic mechanism. A cyclic plasticity-damage model was proposed in this study to predict the stress-strain response of fiber reinforced polymer under cyclic loading. This model is a further extension of the elastic-plastic constitutive model to describe the nonlinear hysteresis behavior proposed by the authors. It can predict the nonlinear responses during loading, hysteresis behavior during unloading and reloading and the ratcheting phenomena under a large number of cycles. As a benchmark problem verification, the experimental data by Kawai et al, were compared with the numerical prediction of the model in this paper. The results show that the model can simulate the ratcheting behavior of carbon fiber/epoxy unidirectional composite under off-axis cyclic loading.
- fiber reinforced polymer /
- cyclic plasticity /
- hysteresis behavior /
- ratcheting effects /
- fatigue damage

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图 1 单向纤维增强聚合物复合材料(FRP)在偏轴循环载荷下应力-应变曲线的典型特征

Figure 1. Typical features of stress-strain curves for unidirectional fiber reinforced polymer (FRP) laminates under off-axis cycle loading

σ_max—Maximum stress; ε, ε^e, ε^p, ε^an, ε^r, ε^an*—Total, elastic, plastic, anelastic, ratcheting and sum of anelastic and ratcheting strain; F(n)—Fatigue modulus

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图 2 循环过程中迟滞回环的不同演化

Figure 2. Different evolution of hysteresis loops during cyclic loading

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图 3 T700S碳纤维/环氧树脂复合材料的初始加载与迟滞环参数确定^[25-26]

Figure 3. Parameters identification of initial loading and hysteresis loop for T700S carbon fiber/epoxy composites^[25-26]

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图 4 计算与测试出的T700S/环氧树脂复合材料的迟滞回环响应(30°试件)^[25-26]

Figure 4. Calculated and measured hysteresis loop response of T700S/epoxy unidirectional laminates (30°)^[25-26]

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图 5 计算与测试出的T700S/环氧树脂复合材料的迟滞回环响应(45°试件)^[25-26]

Figure 5. Calculated and measured hysteresis loop response of T700S/epoxy unidirectional laminates (45°)^[25-26]

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图 6 计算与测试出的T700S/环氧树脂复合材料的迟滞回环响应(45°试件)^[25-26]

Figure 6. Calculated and measured hysteresis loop response of T700S/epoxy unidirectional laminates (45°)^[25-26]

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图 7 计算和测试出的T700S/环氧树脂复合材料棘轮应变-循环周次曲线^[25-26]

Figure 7. Calculated and measured ratcheting strain-cycle curves of T700S/epoxy unidirectional laminates^[25-26]

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图 A-1 T300碳纤维/环氧树脂复合材料的疲劳累积损伤参数确定^[32-33]

Figure A-1. Determination of progressive fatigue damage parameters of T300 carbon fiber/epoxy composites^[32-33]

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表 1 碳纤维/环氧树脂复合材料性能和模型参数(70 ℃)

Table 1. Properties and model parameters of carbon fiber/epoxy composites (70℃)

Material property		Model parameter
Material property		Cycle plastic		Fatigue damage
E₁/GPa	124	a₆₆	1.8	λ₂₂	1.62
E₂/GPa	7.93	A^p	6.35×10⁻¹³	γ₂₂	0.21
G₁₂/GPa	3.74	A^an	4.62×10⁻¹³	λ₁₂	0.70
μ₁₂	0.35	n	5.853	γ₁₂	7.10
Y_T/MPa	33.4	μ	0.10142	A₂₂	0.787
^*Y_C/MPa	123	m	1	B₂₂	0.244
S₁₂/MPa	24.1	σ⁰	22.9	A₁₂	−0.124
		w⁰	0.40	B₁₂	0.251
Notes:E₁—Longitudinal modulus; E₂—Transverse modulus; G₁₂—Shear modulus; u₁₂—Poisson’s ratio; Y_T—Transverse tensile strength; ^*Y_C—Transverse compress strength, from the data of our research group; S₁₂—Shear strength; a₆₆—Shear/transverse plasticity ratio; A^p, A^an,n—Plasticity and anelasticity during initial loading; μ, m, σ⁰, w⁰—Hysteresis loop; λ₂₂, γ₂₂—Transverse fatigue modulus degradation; λ₁₂, γ₁₂—In-plane shear fatigue modulus degradation; A₂₂, B₂₂—Transverse fatigue life; A₁₂,B₁₂—In-plane shear fatigue life.

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