| 2.5D机织复合材料经向和纬向振动疲劳行为对比 |
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| 引用本文： | 王雅娜,任素娥,张琴,刘燕峰,何玉怀. 2.5D机织复合材料经向和纬向振动疲劳行为对比[J]. 复合材料学报, 2023, 40(1): 109-118. DOI: 10.13801/j.cnki.fhclxb.20220223.001 |
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| 作者姓名： | 王雅娜 任素娥 张琴 刘燕峰 何玉怀 |
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| 作者单位： | 中国航发北京航空材料研究院检测研究中心,北京100095;航空材料检测与评价北京市重点实验室,北京100095;中国航空发动机集团材料检测与评价重点实验室,北京100095;中国航发北京航空材料研究院检测研究中心,北京100095 |
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| 基金项目： | 航材院益材基金(KJ53200716) |
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| 摘 要： | 2.5D机织复合材料抗分层、耐冲击,在航空发动机结构上具有巨大的应用前景。本文对一种2.5D机织碳纤维增强双马树脂基复合材料经向和纬向试件,开展了不同名义应力水平下的一阶弯曲共振疲劳试验。试验结果表明：经向试件的振动疲劳性能优于纬向试件,随着应力水平的提高,经向和纬向试件的寿命明显缩短,而固有频率下降百分比增加,试件内部的损伤严重程度和损伤扩展速度都随之提高。2.5D机织复合材料经向和纬向试件在共振疲劳试验过程中的主要失效模式是纱线与基体之间脱粘造成的结构完整性丧失,从而导致试件的刚度持续下降。试件内部损伤的三维电子计算机断层扫描(Computerized tomography,CT)重构图像表明,损伤散布于试件工作段区域,应力水平越高,2.5D机织复合材料经向和纬向试件内部损伤范围越大,损伤程度越高,而且纬向试件内部损伤状态比经向试件严重。利用双对数线性寿命模型,对经向和纬向试件在不同名义应力水平下的共振疲劳试验数据进行拟合,得到2.5D机织复合材料经向和纬向试件共振疲劳应力-寿命(Stress-life,S-N)曲线的数学模型,得到的S-N曲线可用于预测2.5D机织复合材料的寿命。
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| 关 键 词： | 复合材料 碳纤维 2.5D机织 振动疲劳 寿命预测 |
| 收稿时间： | 2021-12-09 |
Comparision of vibration fatigue behaviors of 2.5D woven composites in warp and weft directions |
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| Affiliation: | 1.Aeronautical Material Testing Research Center, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China2.Beijing Key Laboratory of Aeronautical Material Testing and Evaluation, Beijing 100095, China3.Key Laboratory of Aeronautical Material Testing and Evaluation, Aero Engine Corporation of China, Beijing 100095, China |
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| Abstract: | 2.5D woven composites are resistant to delamination and impact, which have great application prospects in aeroengine structures. The first-order bending vibration fatigue tests under different stress levels were carried out for the specimens made of 2.5D woven carbon fiber reinforced bismaleimide resin matrix composites in the warp direction and weft direction, respectively. The experimental results show that the vibration fatigue performance of the warp specimens is better than that of the weft specimens. With the increase of stress levels, the lives of the specimens are shortened obviously, and the decline percentage of natural frequency increase, and the damage degree and damage propagation speed within specimens also increase. In the process of vibration fatigue test, the main failure mode of 2.5D woven composites was the loss of structural integrity caused by the debonding of the yarns and the matrixes, which leaded to the continuous decrease of the stiffness of the specimens. 3D CT reconstruction images of the internal damage of the specimens show that the damages spread throughout in the working section of the specimens. The higher the stress levels are, the greater the internal damage ranges and the higher the damage degrees are. And the internal damage state of the warp specimens is more serious than that of the weft specimens. The mathematical model of stress-life (S-N) curve of vibration fatigue of 2.5D woven composites is obtained by data fitting for vibration fatigue results under different nominal stress levels by using the log-log-linear life model, which can be used to predict the life of 2.5D woven composites. |
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