摘要
老龄飞机中由于多裂纹的产生将导致结构剩余寿命大幅削减。针对如飞机机舱上布有沿纵向铆钉接头的隔板结构,文中给出一种分析多部位损伤结构剩余强度的方法。裂纹扩展模型是分析的基础,文中对两类(单参量和三参量)扩展模型进行讨论,给出裂纹在增量载荷下萌生与稳定扩展的处理方法。基于Irwin和Dugdale裂尖张开位移模型与Swift准则,给出较为完整的分析多部位损伤(multiple site damage,MSD)结构剩余强度的方法。最后,通过对飞机压力舱上的沿纵向铆钉接头的模拟计算,对文中方法进行验证。由分析结果可知,采用文中方法计算得到的剩余强度值与试验值符合得较好,该方法能较为准确有效地对复杂MSD结构的剩余强度进行分析。
The residual life will be reduced because of multiple site damage （MSD）in ageing aircraft. For the fuselage structure with longitudinal riveted joints, a method of computing residual strength of structure with MSD was presented. Basing on two models of cracks growth, one parameter and three parameters models, the wav of analyzing the stage of initiation and stable tearing was discussed in details. Irwin and Dugdale models were used to calculate crack tip opening displacement （ CTOD）. Swift criterion was used to describe the stage of crack link-up. Combining with those fandamenta/fracture mechanics theories, an integrated method to analyze MSD structures＇ residual strength for all stages of crack propagation under increasing loading was expounded. To verify, the method, the model of typical fuselage butt-joint was analyzed by the presented method. The result shows that the method can well cope with the several stages of crack propagation, and the computed results agree well with the experimental ones.
出处
《机械强度》
CAS
CSCD
北大核心
2010年第1期121-124,共4页
Journal of Mechanical Strength
基金
国家自然科学基金(10372082)
航空基金(2006ZD53050
2008ZA53006)资助项目~~
关键词
裂尖张开角
裂尖张开位移
剩余强度
多部位损伤
Crack tip opening angle （CrOA）
Crack tip opening displacement （CTOD）
Residual strength
Multiple site damage（MSD）
