摘要
不同厚度试样的疲劳裂纹扩展试验表明，飞行模拟载荷条件下具有明显的厚度影响。考查了模型对于厚度影响的预测能力。Ｎｅｗｍａｎ的模型具有预测厚度影响的潜力，广义改进的Ｗｉｌｌｅｎｂｏｒｇ模型不含有厚度影响的考虑，即使通过调整约束系数α的方法也难于计及厚度的影响。
atigue crack growth tests were conducted in 7475-T7351 Al alloy with specimens of different thicknesses From flight simulation loading tests a significant thickness effect was ob-served. Crack growth life prediction was carried out using some famous models.It was found that Newman’s model has the capability to predict thickness effect,while the generalized modified Willenborg model is not able to consider thickness effect evenby adjusting constraint coefficient.The physical reason of thickness effect and the modeling consideration are two of the important subjects for successful crack analysis.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第6期757-760,共4页
Acta Aeronautica et Astronautica Sinica
关键词
铝合金
裂纹扩展
尺寸
稳定性
aluminum alloys,crack propagation, dimensional stability
