FATIGUE CRACK-PROPAGATION RATE AT LOW DELTAK OF 2 ALUMINUM SHEET ALLOYS, 2024-T3 AND 7075-T6

被引：22

作者：

MACKAY, TL

机构：

[1] Materials and Producibility Engineering, Douglas Aircraft Company, Long Beach

来源：

ENGINEERING FRACTURE MECHANICS | 1979年 / 11卷 / 04期

关键词：

D O I：

10.1016/0013-7944(79)90134-6

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

For transport aircraft with long lifetimes, crack growth data to implement the durability life requirements in the low ΔK range are needed. This is the region comprising most of the lifetime for the cracks of interest, and it is also the region where there is little data available. Crack growth data in the form of da/dN vs ΔK vs R at constant amplitude for two primary aircraft aluminum sheet alloys, 2024-T3 and 7075-T6 (clad) were measured in laboratory air and 140°F in the low da/dN region 10-8 to 10-5 in./cycle. Crack growth rates were correlated with stress state and with fractographic features. © 1979.

引用

页码：753 / &