单向碳/碳复合材料高温疲劳试验研究

推进技术 ›› 2019, Vol. 40 ›› Issue (2): 456-462.

单向碳/碳复合材料高温疲劳试验研究

陈波,温卫东,崔海涛,张宏建,徐颖

南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016

发布日期:2021-08-15
基金资助:
江苏省高校研究生创新基金(KYLX_0238)；中央高校基本科研基金(1002-56XQA15002)；航空动力基金

Experiment on Fatigue of Unidirectional Carbon/Carbon Composites at Elevated Temperature

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究单向碳/碳的高温疲劳特性，从疲劳损伤力学出发，提出了考虑温度、氧化速率的碳/碳复合材料剩余刚度、剩余强度模型，并开展了碳/碳复合材料［0］16单向板试验件在室温、有涂层700℃和无涂层700℃的拉/拉疲劳试验和剩余强度试验。试验结果表明:单向碳/碳复合材料的剩余刚度曲线呈倒“S”形，材料的刚度退化存在三个阶段；单向碳/碳复合材料在室温和有抗氧化涂层700℃的疲劳加载初期和末期存在刚度突降，中期的刚度无明显退化；单向碳/碳复合材料在室温的疲劳刚度退化小于10%，而有抗氧化涂层单向碳/碳复合材料700℃的刚度退化超过30%；无抗氧化涂层单向碳/碳复合材料在疲劳中期存在明显刚度退化，末期无刚度突降。模型的拟合结果表明:复合材料高温剩余刚度、剩余强度模型能够很好地预测单向碳/碳复合材料在室温和700℃的剩余刚度、剩余强度变化。

关键词: 高温；疲劳试验；碳/碳复合材料；单向板；剩余刚度；剩余强度

Abstract: In order to study high temperature fatigue characteristic of unidirectional carbon/carbon composites， the residual stiffness model and residual strength model of carbon/carbon composites considering temperature and oxidation rate were proposed from fatigue damage mechanics. Tensile/tensile fatigue experiment and residual strength experiment of ［0］16 unidirectional carbon/carbon composite laminates specimens with and without anti-oxidation coating also were carried out at room temperature and 700℃. The experiment results show that residual stiffness curves of unidirectional carbon/carbon composites have three stages and present lying “S”. The stiffness of unidirectional carbon/carbon composites with anti-oxidation coating decline sharply in initial stage and last stage of fatigue at room temperature and 700℃，but the stiffness have no obvious degradation in middle stage of fatigue. The stiffness degradation of unidirectional carbon/carbon composites is less than 10% at room temperature. However， the stiffness degradation of unidirectional carbon/carbon composites with anti-oxidation coating become more than 30% at 700℃. The unidirectional carbon/carbon composites without anti-oxidation coating exist stiffness degradation obviously， and there is no stiffness sudden drop when material access fatigue life. The fitting results of the model show that the high temperature residual stiffness model and residual strength model of composites can predict well on residual stiffness and residual strength changes of unidirectional carbon/carbon composites at room temperature and 700℃.

Key words: High temperature；Fatigue experiment；Carbon/carbon composites；Unidirectional laminates；Residual stiffness；Residual strength

陈波,温卫东,崔海涛,张宏建,徐颖. 单向碳/碳复合材料高温疲劳试验研究[J]. 推进技术, 2019, 40(2): 456-462.

CHEN Bo,WEN Wei-dong,CUI Hai-tao,ZHANG Hong-jian,XU Ying. Experiment on Fatigue of Unidirectional Carbon/Carbon Composites at Elevated Temperature[J]. Journal of Propulsion Technology, 2019, 40(2): 456-462.

参考文献

[1] 李贺军. 碳/碳复合材料[J]. 新型碳材料, 2001, 16(2): 70-80.
[2] 李成功, 傅恒志. 航空航天材料[M]. 北京: 国防工业出版社, 2002.
[3] 杨尊社, 卢刚认, 曲德全, 等. C/C复合材料的磷酸盐与硼系涂料的防氧化研究[J]. 材料保护, 2001, 34(3).
[4] Liu C, Cheng L, Luan X, et al. Real-Time Damage Evaluation of a SiC Coated Carbon/Carbon Composite under Cyclic Fatigue at High Temperature in an Oxidizing Atmosphere[J]. Materials Science and Engineering: A, 2009, 524(1-2): 98-101.
[5] Liu C, Cheng L, Luan X, et al. High-Temperature Fatigue Behavior of SiC-Coated Carbon/Carbon Composites in Oxidizing Atmosphere[J]. Journal of the European Ceramic Society, 2009, 29(3): 481-487.
[6] 朱元林, 温卫东, 刘礼华, 等. 碳/碳复合材料疲劳损伤失效试验研究[J]. 复合材料学报, 2016, 33(2):386-393.
[7] Yang J N, Jones D L, Yang S H, et al. A Stiffness Degradation Model for Graphite/Epoxy Laminates[J]. Journal of Composite Materials, 1990, 24: 753-769.
[8] Lee J W, Allen D H, Harris C E. Internal State Variable Approach for Predicting Stiffness Reductions in Fibrous Laminated Composites with Matrix Cracks[J]. Journal of Composite Materials, 1989, 23: 1273-1291.
[9] Wu W, Lee L J, Choi S T. A Study of Fatigue Damage and Fatigue Life of Composite Laminates[J]. Journal of Composite Materials, 1996, 30: 123-137.
[10] Yao W X, Himmel N. A New Cumulative Fatigue Damage Model for Fibre-Reinforced Plastics[J]. Composites Science and Technology, 2000, 60(1): 59-64.
[11] Han K S, Hwang W. Fatigue Life Prediction and Failure Mechanisms of Composite Materials[J]. Advanced Composite Materials, 1992, 2(1): 29-50.
[12] Bucinell R B. Development of a Stochastic Free Edge Delamination Model for Laminated Composite Materials Subjected to Contant Amplitude Fatigue Loading[J]. Journal of Composite Materials, 1998, 32(12): 1138-1156.
[13] Shokrich M M, Lessard L B. Progressive Fatigue Damage Modeling of Composite Materials, Part II: Material Characterization and Model Verification[J]. Journal of Composite Materials, 2000, 34(13): 1081-1116.
[14] Shokrich M M, Lessard L B. Multiaxial Fatigue Behaviour of Unidirectional Plies Based on Uniaxial Fatigue Experiments, I: Modeling[J]. International Journal of Fatigue, 1997, 19: 201-207.
[15] Shokrich M M, Lessard L B. Multiaxial Fatigue Behaviour of Unidirectional Plies Based on Uniaxial Fatigue Experiments, II: Experimental Evaluation[J]. International Journal of Fatigue, 1997, 19: 209-217.
[16] Mao H, Mahadevan S. Fatigue Damage Model of Composite Materials[J]. Composite Structures, 2002, 58(4): 405-410.
[17] Lee J H. An Experimental and Analytical Investigation of the Stiffness Degradation of Graphite/Epoxy Composite Laminates under Cyclic Loading[D]. Washington:The George Washington University, 1989.
[18] 王丹勇. 层合板接头损伤失效与疲劳寿命研究[D]. 南京:南京航空航天大学, 2006.
[19] 廉伟, 姚卫星. 复合材料层压板剩余刚度-剩余强度关联模型[J]. 复合材料学报, 2008, 25(5): 151-156.　　　　　　　　　　　　　　收稿日期:2018-05-02；修订日期:2018-06-15。基金项目:江苏省高校研究生创新基金(KYLX_0238)；中央高校基本科研基金(1002-56XQA15002)；航空动力基金 (6141B090304)。通讯作者:陈波,博士生,研究领域为先进复合材料结构设计技术。E-mail: chenbocepe@nuaa.edu.cn(编辑:朱立影)