摘要
复合材料层合板疲劳损伤机理和寿命预测是关系到现代航空结构损伤容限设计的关键问题。通过对复合材料层合板疲劳损伤特征研究,从应变等效性出发,结合经典刚度降法,建立层合板疲劳寿命预测两阶段宏观唯象模型,弥补了经典刚度降法和S-N曲线模型的不足。应用此模型对新型的缝合复合材料层合板进行了相关分析与研究,并将预测结果与试验结果进行了对比。结果表明,所建立的疲劳寿命预测模型结果与试验结果吻合良好,可为缝合复合材料的失效分析与工程应用奠定一定的理论基础。
The fatigue damage mechanism and life prediction of composite laminates are critical problems for airframe damage tolerance design. According to the fatigue damage characteristics of composite laminates and based on the typical stiffness reduction method, a two-phase fatigue life predicting model was established. This model made up the disadvantages of the typical stiffness reduction method and the S-N model. The model was used to study the stitched composite laminates, and the predicted results were compared with the test results to verify the model. It is shown that the predicted results obtained by this model are consistent with the test data. The relative error is only 30.9%. This study can lay a theoretical basis for the failure analysis and engineering application of stitched composite laminates.
出处
《失效分析与预防》
2008年第4期8-11,共4页
Failure Analysis and Prevention
基金
国家自然科学基金项目(10672009)
航空基础科学基金项目(05B51044)
北京航空航天大学凡舟基金项目(20060501)
