复合材料层合板疲劳逐渐累积损伤寿命预测方法

徐颖; 温卫东; 崔海涛

复合材料层合板疲劳逐渐累积损伤寿命预测方法

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2006-04-05
- 修回日期: 2006-06-11
- 刊出日期: 2007-04-28

Progressive fatigue damage analysis method of laminated composites

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

摘要

摘要: 针对疲劳载荷作用下的纤维增强复合材料层合板, 发展了疲劳逐渐累积损伤寿命预测方法.该方法主要包括应力分析、失效分析及材料性能下降三部分.其中, 应力分析是通过三维有限元数值分析技术实现的;失效分析采用改进的Hashin静态失效准则判断疲劳损伤的产生和扩展;材料性能是基于突降和渐降两种准则进行退化的.所发展的方法可以预测不同铺层顺序、不同几何尺寸的复合材料层合结构在疲劳载荷下的损伤起始、扩展、直至结构最终破坏整个过程, 并预测其疲劳寿命.同时, 在ANSYS软件平台上, 开发了相应的参数化复合材料层板结构的疲劳逐渐损伤分析程序.与已有文献结果比较, 误差在10%以内.
- 航空、航天推进系统 /
- 逐渐损伤 /
- 复合材料层合板 /
- 疲劳 /
- 数值模拟
Abstract: A progressive fatigue damage analysis method was developed to predict damage propagation and life of laminated composites subjected to constant amplitude cyclic loading. It consists of stress analysis, fatigue damage analysis and material property degradation technique. Stress analysis of composite laminates was performed by creating a three-dimensional finite element model using the ANSYS FE code. Modified Hashin failure criterion was used to fatigue damage analysis. The rules of sudden degradation and gradual degradation were applied in material property degradation technique for modifying element stiffness and strength. Simulation results show that this progressive fatigue damage method is competent for simulating progressive damage and predicting fatigue life of laminated composites with arbitrary geometry and ply stacking sequence. A parametric progressive fatigue damage analysis programme was developed based on the ANSYS FE code. The error between the predicted results and the test data is within 10%.
- aerospace propulsion system /
- progressive damage /
- laminated composites /
- fatigue /
- numerical simulation

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参考文献(13)

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