碳纤维增强碳化硅mini复合材料超高温塑性本构关系实验和理论研究

李思儒; 吉洪蕾; 马智棋; 成天宝; 陈立明

doi:10.21656/1000-0887.460072

碳纤维增强碳化硅mini复合材料超高温塑性本构关系实验和理论研究

doi: 10.21656/1000-0887.460072

重庆大学航空航天学院，重庆 400030

(我刊编委陈立明来稿)

基金项目:

国家自然科学基金 12027901

国家自然科学基金 12272069

国家自然科学基金 11802019

详细信息

作者简介:
李思儒(1999—)，男，硕士生(E-mail: lisrhnny@163.com)

通讯作者:
成天宝(1987—)，男，研究员，博士，博士生导师(通信作者. E-mail: tbcheng@cqu.edu.cn)

中图分类号: O34
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- 文章访问数: 53
- HTML全文浏览量: 11
- PDF下载量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2025-04-10
- 修回日期: 2025-05-01
- 刊出日期: 2026-05-01

Ultra-High-Temperature Plastic Constitutive Relations of Carbon Fiber Reinforced Silicon Carbide Minicomposites: Experiment and Modeling

College of Aerospace Engineering, Chongqing University, Chongqing 400030, P.R. China

(Contributed by CHEN Liming, Member of the Editorial Board of AMM)

摘要

摘要: 先进的陶瓷基复合材料具有耐超高温、抗腐蚀、高的比强度和高的比刚度等优异性能，是新一代高超声速飞行器热防护材料和结构的重要候选材料. 然而，陶瓷基复合材料复杂的微观结构和多种损伤机制使其本构研究面临诸多挑战. Mini复合材料是多尺度研究中的重要桥梁，研究其力学性能对先进陶瓷基复合材料的研发和服役安全可靠性评价具有重要意义. 基于间接感应加热技术，首次开展了惰性环境2 200 ℃下C/PyC/SiC mini复合材料拉伸性能测试，揭示了陶瓷基复合材料在服役超高温极端环境下的塑性变形行为. 采用三参数Weibull概率统计模型表征基体的随机开裂，通过剪滞模型计算纤维和基体中的应力分布，考虑纤维束的超高温非线性变形和残余热应力影响，建立了C/PyC/SiC mini复合材料超高温塑性细观本构模型，并将理论预测结果和实验结果对比，对模型进行了验证. 该研究不仅能够丰富陶瓷基复合材料的力学理论体系，还将为其在高超声速飞行器上的服役可靠性评估和寿命预测提供实验和理论支撑.
- 陶瓷基复合材料 /
- 超高温极端环境 /
- 塑性本构关系
Abstract: Advanced ceramic matrix composites have excellent properties, such as resistance to ultra-high temperatures and corrosion, as well as high specific strength and stiffness. They are important candidates for thermal protection materials and structures of new-generation hypersonic vehicles. However, ceramic matrix composites have complex microstructures and various damage mechanisms, which make the study of their constitutive relations challenging. Minicomposites are the critical link in the multi-scale study of ceramic matrix composites. The study on their mechanical behaviors is important to the development and evaluation of security and reliability of advanced ceramic matrix composites. The tensile properties of C/PyC/SiC minicomposites were measured at 2 200 ℃ in inert atmospheres for the first time based on the indirect induction heating technology. The plastic deformation behaviors of ceramic matrix composites under ultra-high-temperature extreme environments were revealed. The random cracking of matrix was characterized by a 3-parameter Weibull model. The stress distributions of fiber and matrix were calculated based on the slip-lag model. The effects of ultra-high-temperature nonlinear deformation of fiber bundles and residual thermal stresses in the composites were characterized. An ultra-high-temperature plastic mesoscale constitutive model was established for C/PyC/SiC minicomposites and verified. The study is useful for the development of mechanics for ceramic matrix composites and provides experimental and theoretical supports for the reliability evaluation and life prediction of ceramic matrix composites on the hypersonic vehicles.
- ceramic matrix composite /
- ultra-high-temperature extreme environment /
- plastic constitutive
edited-by

edited-by
注释:

1) (我刊编委陈立明来稿)

HTML全文

图 1 C/PyC/SiC mini复合材料拉伸模型

Figure 1. The tensile model for C/PyC/SiC minicomposites

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图 2 计算流程图

Figure 2. The flowchart of calculations

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图 3 实验测得的拉伸应力-变形曲线

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 3. Tensile stress-deformation curves measured experimentally

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图 4 C/PyC/SiC mini复合材料微观图

Figure 4. Microscopic photos of C/PyC/SiC minicomposites

下载: 全尺寸图片幻灯片

图 5 理论预测得到的C/PyC/SiC mini复合材料惰性环境2 200 ℃时的拉伸应力-变形曲线和实验结果的对比

Figure 5. Comparison between the tensile stress-deformation curves of C/PyC/SiC minicomposites at 2 200 ℃ in inert atmosphere calculated by theory and measured by experiment

下载: 全尺寸图片幻灯片

图 6 不同变量对C/PyC/SiC mini复合材料惰性环境2 200 ℃时的拉伸应力-变形行为的影响

Figure 6. Effects of different factors on the tensile stress-deformation behaviors of C/PyC/SiC minicomposites at 2 200 ℃ in inert atmosphere

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表 1 计算所用材料参数

Table 1. Material parameters used in the calculations

parameter	value	parameter	value
L₀/mm	200	L_HT/mm	60
V_f/%	23	V_m/%	77
r_f/μm	3.5	E_fRT/GPa	211
E_mRT/GPa	276	E_m(2 200 ℃)/GPa	16
α_m(2 200 ℃)/(10^-6 /℃)	4.50	α_f(2 200 ℃)/(10^-6 /℃)	2.56
τ(2 200 ℃)/MPa	3	k₁/(10^-3·mm·MPa^-1)	1.06
a/(10^-3·mm·MPa^-2)	6.01	b/(10^-3·mm·MPa^-1)	2.50
T/℃	2 200	T_p/℃	1 000
C_p/(10^-3·mm·N^-1)	2.90	σ_b/MPa	10
m₀	5	L_b/m	1

下载: 导出CSV

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