某直升机进口材料断裂性能测定技术  

Determine Technology for Fracture Capability of a Importation Material on the Helicopter

作　　者：曾本银[1] 朱定金[1] 喻溅鉴[1] 张伟[1] 

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《直升机技术》2007年第4期13-18,共6页Helicopter Technique

摘　　要：本文在总结传统疲劳裂纹扩展曲线的基础上,讨论了四参数全范围da/dN曲线公式。根据断裂性能测试标准,分别测试了直升机桨叶根部材料断裂韧性K1c,3个应力比下的裂纹扩展门槛值△Kth和裂纹扩展速率da/dN;再利用多元线性回归法对试验数据进行了曲线拟合,分别得到了断裂等寿命曲线和四参数全范围da/dN曲线公式。A four-parameter curve to describe the full range of fatigue crack growth rate is adopted to represent the results of fatigue crack growth rate tests based on the conventional method.Based on the fracture test standard,fracture roughnessKIC,fracture threshold value Kth and crack growth rate da/dN at three different stress ratio are determined for a metallic material on the root of helicopter rotor blade.The formula of fracture constant life curve and the four-parameter full range da/dN.Forman curve formula are derived by using the multivariate linear regression.

关 键 词：裂纹扩展 断裂韧性 门槛值 线性回归法 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]