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论文:2016,Vol:34,Issue(2):222-226 |
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引用本文： |
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马玉娥, 王博, 熊晓枫. 玻璃纤维铝合金层板(FMLs)的疲劳损伤特性及S-N曲线[J]. 西北工业大学学报 |
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Ma Yu'e, Wang Bo, Xiong Xiaofen. Experimental Study of Fatigue Damage of Glass-Fiber Reinforced Aluminum Laminates (FMLs)[J]. Northwestern polytechnical university |
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| 玻璃纤维铝合金层板(FMLs)的疲劳损伤特性及S-N曲线 |
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| 马玉娥1, 王博1, 熊晓枫2 |
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1. 西北工业大学 航空学院118号, 陕西 西安 710072;
2. 中航工业成都飞机设计研究所, 四川 成都 610041 |
| 摘要: |
| 根据国内外标准和参考文献,针对玻璃纤维增强铝合金层板(FMLs)的特点设计出FMLs疲劳试验件,进行了不同载荷下的R=0.1等幅拉-拉疲劳试验。疲劳试验过程中FMLs最先在表面铝层内出现裂纹,随后表面铝层可见多条裂纹。随着循环载荷数的增加,裂纹不断扩展,并在界面出现分层现象,然后分层损伤快速扩展直至完全断裂破坏。测得了FMLs的疲劳裂纹起裂寿命和裂纹扩展寿命,给出了其疲劳寿命的规律性。得到了FMLs和同样厚度碳纤维复合材料CCF300的S-N曲线,并进行了对比。FMLs的疲劳寿命随载荷变化平缓,近似成对数趋势;在载荷大于400 MPa时FMLs的疲劳寿命与CCF300碳纤维复合材料层板相当;当疲劳载荷最大值低于300 MPa,FMLs的疲劳寿命比CCF300复材板要低。为飞机结构设计师们提供了材料基础性能和信息。 |
| 关键词:
玻璃纤维增强铝合金层板
疲劳裂纹起裂寿命
裂纹扩展寿命
分层扩展
S-N曲线
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| Experimental Study of Fatigue Damage of Glass-Fiber Reinforced Aluminum Laminates (FMLs) |
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| Ma Yu'e1, Wang Bo1, Xiong Xiaofen2 |
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1. College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. AVIC Chengdu Aircraft Design & Research Institute, Chengdu 610041, China |
| Abstract: |
| According to domestic and foreign standards and references, fatigue experimental samples of glass-fiber reinforced aluminum laminates(FMLs) were designed according to its features, and constant amplitude tension-tension fatigue experiments were performed under different fatigue loads. During testing, cracks appeared firstly on the surface aluminum layers and then many cracks were found on the surfaces. With cycles increasing, cracks grew and then the delamination developed fast until samples were broken completely. Fatigue initiation life and crack growth life of FMLs were measured and compared and their features were given. S-N curves of FMLs and CCF300 with the same thickness were obtained and compared. Fatigue life of each FML changes slowly with loads and almost seems to be logarithmic function line. When the load is higher than 400 MPa, FML has the same level fatigue life as CCF300, while its fatigue life is much lower than CCF300 if the load is smaller than 300MPa. All these provide, we believe, information useful to aircraft designers. |
| Key words:
aluminum
delamination
design
design of experiments
fatigue crack propagation
fatigue damage
fatigue of materials
laminates
measurements
sampling
crack growth life
delamination growth
fatigue initiation life
fractograph
FMLs
S-N curve
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| 收稿日期: 2015-10-20
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 马玉娥(1975-),女,西北工业大学教授、博士生导师,主要从事固体力学、结构疲劳与断裂复合材料力学的研究。
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| 作者相关文章 |
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| 马玉娥 在本刊中的所有文章 |
| 王博 在本刊中的所有文章 |
| 熊晓枫 在本刊中的所有文章 |
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相关文献: |
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1．夏仲纯, 马玉娥, 云双, 熊晓枫.玻璃纤维增强铝合金层板的裂纹扩展特性研究[J]. 西北工业大学学报, 2013,31(6): 891-895 |
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