随机疲劳载荷谱加重对单裂纹扩展寿命的影响  

Effect on Single Crack Growth Lifetime with Random Fatigue Load Spectra Enhancement

作　　者：张文东[1] 董登科[1] 陈莉[1] 李三元[1] ZHANG Wen-dong;DONG Deng-ke;Chen Li;Li San-yuan(Aircraft Strength Research Institute of China,Xi'an 710065,China)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《科学技术与工程》2018年第11期326-331,共6页Science Technology and Engineering

摘　　要：疲劳载荷谱加重已成为加速试验的重要研究内容;它对单裂纹扩展影响的研究很有价值。以Paris裂纹扩展模型为基础,进行理论推导。提出了单裂纹在加重谱作用下裂纹扩展寿命的估算方法,分别是基于循环次数的次估算法和基于谱块数的块估算法。利用原始载荷谱的试验结果分别计算得到加重谱下的两种估算结果,设计试验对估算结果进行验证,证明了方法的可行性。研究结果可作为加快全尺寸飞机结构疲劳试验的参考。Fatigue load spectra enhancement has played an important role in the study of accelerated test,with which the research on the effect on crack growth is very valuable.The estimate methods of single crack propagation life under enhanced load spectra was put forward base on Paris crack propagation model and by theory deducibility.The methods were estimate method based on cycle numbers and estimate method based on spectrum numbers respectively.the two estimated results were carried out by making use of the test result of original load spectra.Designing test validated the feasibility of the estimated methods.The investigation can be a useful reference for the fatigue test of the full-scale airplane structure.

关 键 词：载荷谱加重 裂纹扩展模型 裂纹扩展寿命 估算方法 试验验证 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程]