带裂纹层合板复应力强度分析

胡互让; 吴承平

带裂纹层合板复应力强度分析

胡互让¹,
吴承平²

1.
美国西拉库斯大学机械航空和制造工程系;
2.
重庆交通学院 630074

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出版历程
- 收稿日期: 1994-11-25
- 刊出日期: 1996-02-15

Analysis of Complex Stress Intensities for Cracked Laminates

Hu Hurang¹,
Wu Chengping²

1.
Department of Mechanical, Aerospace and Manufacturing Ellgineering, Syracuse Universit, Syracuse, NY 13244, USA;
2.
Chongqing Jlaotong institute, Chongqing 630074, P. R. China

摘要

摘要: 本文用经典板理论求得了复合材料层合板的界面应力强度因子.利用裂纹尖端能量释放率和复应力强度因子间的关系,给出最一般的复合材料层合板,在相应外荷载和模型混合参数下的复应力强度因子的一个封闭形式的解.然后提出确定这一模型混合参数的步骤,给出某些层合板的数值结果.并给出在相应外荷载下的小范围接触条件.特别证明了界面韧度曲线的对称性质.最后讨论振荡指数消失后,预计的断裂荷载的精确性.还通过一个实例表明β=0法的有效性和局限性.
- 复合材料 /
- 层合板 /
- 复应力强度因子 /
- 能量释放率 /
- 界面裂纹
Abstract: Classical plate theory has been used to find out interfacial stress intensity factors in composite laminates. By using a well-known relation between the crack-tip energy release rate and the complex stress intensity factor. a closed-form solution for complex. Stress intensity in terms of external loading and a mode mix parameter for fairly. general composite laminates is given. Then a procedure for determining this mode mix. parameter is presented. followed by numerical results for some laminates. Small scale contact condition is expressed in terms of external loading In particular, a symmetric property of interfacial toughness curye is proven. Finally. the accuracy of failure load predicled by elininating oscllation index is discussed. and an example is presented to show the validity and limitation of β=1 approximation.
- composite materials /
- laminates /
- complex stress intensity factor.energy release rate /
- inlerface Crack /

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参考文献(22)

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