FATIGUE LIFE PREDICTION METHOD FOR IMPACTED LAMINATES  

复合材料层合板冲击及冲击后疲劳寿命预测方法(英文)

作　　者：徐颖[1] 温卫东[1] 崔海涛[1] 

机构地区：[1]南京航空航天大学能源与动力学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2011年第1期87-93,共7页南京航空航天大学学报（英文版）

摘　　要：The existing models are established based on the fatigue behavior of impacted laminates.It makes them unsuitable for the general use.So,a general 3-D progressive damage fatigue life prediction method for impacted laminates is developed based on the progressive damage theory and the fatigue behavior of unimpacted unidirectional plies.The model can predict the fatigue life of laminated composites with different ply parameters,geometry,impact damage,and fatigue loading conditions.In order to obtain the impact damage information in the case that no impact test data is available,a whole damage process analysis method for laminated composites under the impact loading and the fatigue loading is analyzed.The predicted damage statuses of composite laminates can be used to analyze the post-impact fatigue life.A parametric modeling program is developed to predict the impact damage process and the fatigue life of impacted laminates based on the whole damage process analysis method.The most relative error between the prediction and the test results is 7.78%.现有含冲击损伤复合材料层合板的寿命预测方法是建立在冲击后复合材料层合板的疲劳性能基础之上的,导致模型和方法不具有通用性。因此,针对含冲击损伤的复合材料层合板,基于逐渐累积损伤理论和无损单向板的疲劳特性,建立一种具有普遍适用性的三维逐渐累积损伤的疲劳寿命预测方法。该方法可对不同铺层参数、不同几何尺寸以及不同冲击条件下层合板的疲劳寿命进行预测。为了在缺少冲击试验时也能实现受到冲击载荷后层合板的疲劳寿命预测,对层合板在冲击载荷及冲击后疲劳载荷作用下的破坏进行全程分析,将预测得到的冲击损伤状态用于分析冲击后的疲劳寿命。同时基于全程分析的方法,开发了参数化的复合材料层合结构冲击及冲击后疲劳破坏模拟程序。与试验对比,最大误差为7.78%。

关 键 词：laminated composites fatigue testing IMPACT progressive damage 

分 类 号：TB332[一般工业技术—材料科学与工程]