压-压疲劳载荷下CFRP层合板表面红外辐射特征

doi:10.7527/S1000-6893.2020.24239

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压-压疲劳载荷下CFRP层合板表面红外辐射特征

杨正伟^1,2, 赵志彬¹, 李胤³, 宋远佳³, 寇光杰¹, 李磊⁴, 程鹏飞⁴

1. 火箭军工程大学导弹工程学院, 西安 710038;
2. 西安交通大学机械工程学院, 西安 710049;
3. 中国空气动力研究与发展中心, 绵阳 621000;
4. 中国飞机强度研究所, 西安 710065

收稿日期:2020-05-18 修回日期:2020-06-16 出版日期:2021-05-15 发布日期:2020-07-27
通讯作者: 李胤 E-mail:DIYLLLLY@163.com
基金资助:
国家自然科学基金（51575516）；中国博士后科学基金（2019M650262）；陕西省自然科学基金（2020 JM-354）；航空科学基金（201803U8003）

Infrared radiation characteristics of CFRP laminate surface under compressive fatigue load

YANG Zhengwei^1,2, ZHAO Zhibin¹, LI Yin³, SONG Yuanjia³, KOU Guangjie¹, LI Lei⁴, CHENG Pengfei⁴

1. School of Missile Engineering, Rocket Force University of Engineering, Xi'an 710038, China;
2. School of Mechanical Engineering, Xi'an Jiaotong University, Xi'an 710049, China;
3. China Aerodynamics Research and Development Center, Mianyang 621000, China;
4. Aircraft Strength Research Institute, Xi'an 710065, China

Received:2020-05-18 Revised:2020-06-16 Online:2021-05-15 Published:2020-07-27
Supported by:
National Natural Science Foundation of China (51575516); China Postdoctoral Science Foundation (2019M650262); Natural Science Foundation of Shaanxi Province (2020 JM-354); Aeronautical Science Foundation of China (201803U8003)

摘要/Abstract

摘要： 为探究含冲击损伤CFRP层合板在循环交变载荷下的损伤演化规律，基于热力耦合效应研究了含损伤CFRP层合板疲劳过程中的表面红外辐射特征。以压-压疲劳试验模拟交变载荷，采用红外热成像方法分析了疲劳过程中含损伤CFRP层合板的热图序列和温度数据，结果表明：随着疲劳次数的增加，损伤沿垂直疲劳载荷方向演化，热斑颜色逐渐加深，初始冲击损伤形状逐渐演化为椭圆状，最后热斑横向端部出现"尖点"；试件最大表面温差演化整体呈"快速上升-缓慢上升-快速上升"规律，最后出现跳升，其中热斑尖点、最大表面温差跳升可被视为结构疲劳破坏的前兆；含损伤CFRP层合板疲劳破坏时，其最大表面温差主要与纤维和基体种类有关，而试件铺层方式相较于纤维基体类别对最大表面温差无明显影响。研究揭示了冲击后CFRP层合板在疲劳载荷作用下的损伤演化规律，为飞行器复合材料结构的剩余疲劳寿命评估与损伤容限设计奠定了基础。

关键词: CFRP, 等幅疲劳试验, 红外热成像, 疲劳寿命, 热图序列

Abstract: To explore the damage evolution rule of impact-damaged CFRP laminates under cyclic alternating load, we studied the surface infrared radiation characteristics of damaged CFRP laminates during fatigue based on the thermodynamic coupling effect. Using the infrared thermal image method, we analyzed the heat map sequences and temperature data of the damaged CFRP laminated plate during fatigue with the pressure-pressure fatigue test simulating the alternating load. Results show that with the increase of fatigue times, the damage evolves along the vertical direction of the fatigue load, the color of the hot spot gradually deepens, the initial impact damage slowly evolves into an elliptical shape, and finally a "sharp point" appears at the end of the hot spot. The maximum surface temperature difference of the specimen as a whole shows the rule of "fast rise-slow rise-fast rise", finally leading to a jump. The "sharp point" on the hot spot and the maximum surface temperature difference jump can be regarded as the precursor of structural fatigue failure. When the CFRP laminates are damaged, the maximum surface temperature difference is mainly related to the types of the fiber and the matrix, while the laying-out mode of the specimens has no significant influence on the types of fiber matrix. The study reveals the damage evolution law of CFRP laminates under fatigue load after impact, laying a foundation for the residual fatigue life evaluation and damage tolerance design of aircraft composite structures.

Key words: CFRP, constant amplitude fatigue tests, infrared thermal imaging, fatigue life, heat map sequences

中图分类号:

V45
TB332

杨正伟, 赵志彬, 李胤, 宋远佳, 寇光杰, 李磊, 程鹏飞. 压-压疲劳载荷下CFRP层合板表面红外辐射特征[J]. 航空学报, 2021, 42(5): 524239-524239.

YANG Zhengwei, ZHAO Zhibin, LI Yin, SONG Yuanjia, KOU Guangjie, LI Lei, CHENG Pengfei. Infrared radiation characteristics of CFRP laminate surface under compressive fatigue load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(5): 524239-524239.

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压-压疲劳载荷下CFRP层合板表面红外辐射特征

Infrared radiation characteristics of CFRP laminate surface under compressive fatigue load

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