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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。
On the basis of summarizing the traditional fatigue crack growth curve, this paper discusses the formula of da / dN curve with full range of four parameters. According to the test standard of fracture performance, the crack growth threshold △ Kth and the crack growth rate da / dN at three stress ratios of helicopter blade root were measured respectively. The test data were tested by multiple linear regression Fitting, respectively, fracture life curve and four parameters of the full range da / dN curve formula.