论文部分内容阅读
本文讨论了复杂谱载荷作用下裂纹扩展寿命预测的问题,选择了到目前为止功能较强的两种裂纹扩展模型:修正的广义的Willenborg模型和修正的Maarse模型;并对这两个模型就塑性区计算与超载延缓区计算等方面作了改进。 将本文改进后的上述两个模型应用于歼击机真实飞行谱载荷下裂纹扩展寿命的计算,计算结果与实验结果的比较表明:经本文改进后的模型功能强、精度较高、使用方便,可推广应用于各种复杂谱载荷下疲劳裂纹扩展预测的工程实践中去。
In this paper, the problem of crack propagation life prediction under complex spectral loading is discussed. Two kinds of crack propagation models with strong functions so far are selected: the modified generalized Willenborg model and the modified Maarse model; and the plasticity Area calculation and overload delay area calculation has been improved. The above two improved models are applied to the calculation of crack propagation life under the real flying spectrum of fighter aircraft. Comparing the calculated results with the experimental results, it is shown that the improved model has the advantages of strong function, high precision, convenient use and popularization It is applied to the engineering practice of fatigue crack growth prediction under various complex spectral loads.