LY12CZ、LC4CS铝合金板材疲劳裂纹扩展特性研究

A STUDY ON STATISTICAL NATURE OF FATIGUE CRACK GORWTH FOR THE LY12CZ AND LC4CS ALLOYS ALUMINUM

已完成了LY12CZ及LC4CS材料4种厚度(5mm、4mm、3mm、2mm)共66件试件的疲劳裂纹扩展试验。用Weibull分布给出了在给定置信度水平下的P-da/dN-△K曲线及不同可靠度下Paris公式的拟合值参量。并对同一可靠度下相同材料、不同厚度的裂纹扩展统计特性作了比较,其结果可供飞机结构耐久性、损伤容限及可靠性设计时参考使用。

Fatigue Tack growth tests for more than sixty specimens have been completed, which are made from LY12CZ and LC4CS with thickness of 5mm, 4mm, 3mm, 2mm respectively. The P-da / dN-ΔK curves are obtained by using Weibnll distribution under a given confidence. The parameters for Paris formula with different reliabilities are also obtained. Furthermore a comparison is made to the statistical nature of fatigue crack propagation for the same material with different thicknesses and the same reliability. These results can be used as an important reference in durability damage tolerance design and reliability design of aircraft structures.