某型直升机主桨叶裂纹扩展寿命研究

详细信息

Research of Crack Growth Life for Certain Helicopters Main Blade

摘要: 为保证某型直升机延寿后的飞行安全, 对其疲劳危险部位根部接头进行了材料断裂性能试验, 并对试验数据进行分析处理。通过计算, 对比研究了不同裂纹扩展公式下的裂纹扩展寿命。采用考虑因素较全面的, 且具有较高可靠度的全范围Forman公式进行裂纹扩展寿命分析, 得到不同风险率下的裂纹扩展寿命, 并给出了适合的检查周期。
- 裂纹扩展模型 /
- 断裂性能试验 /
- 可靠度 /
- 裂纹扩展寿命 /
- 检查周期
Abstract: In order to guarantee the fly safety of certain helicopters main blade after prolonging life, the materials rupture performance test was carried on the fatigue danger parts of the helicopters root tie-in, and then the test data were analyzed and disposed. Through calculation, different crack growth lives among different crack growth formulas were contrasted. Then the crack growth lives were analyzed with the crack growth formula of full range Forman formula with reliabilities, and the inspection periods were given.
- Crack growth model /
- Rupture performance test /
- Reliability /
- Crack growth life /
- Inspection period

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