摘要
在大量拉-压超载实验的基础上导出考虑拉-压超载中压缩载荷影响的参数———超载截止比γSR的计算式,并提出简单超载截止比γSO的实验测定方法。将参数γSR用于裂纹扩展寿命预测模型。
Based on plenty of tensile-compressive overload test,a formula of overload shut-off ratio γ SR ,the parameter which takes account of reducing overload retardation effect by compressive load,is proposed.For delermining the value of overload shut-off ratio γ SO of single overload,a test method is suggested here as well.It is shown that the prediction of crack propagation life with the parameter γ SR involved in is well correlated with the test results of random load spectra.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第2期182-187,共6页
Acta Aeronautica et Astronautica Sinica
关键词
超载比
裂纹扩展
疲劳裂纹
飞机结构
tensile-compressive overload,overload ratio,crack propagation