论文部分内容阅读
对飞机结构耐久性和安全性有重要影响的紧固孔原始疲劳质量进行了分析，建立了制孔技术与紧固孔原始疲劳质量的内在联系。提出用满足双９５％要求的当量初始裂纹尺寸ａ；值来定量描述紧固孔原始疲劳质量。给出通过紧固孔原始疲劳质量评定和符合性检查来选择或验证制孔技术的方法。
The original fatigue quality of the fastening hole, which has an important influence on the durability and safety of the aircraft structure, is analyzed, and the inherent relationship between the hole making technology and the original fatigue quality of the fastening hole is established. Proposed to meet the double 95% of the requirements of the equivalent initial crack size a; value to quantitatively describe the original fatigue quality of the fastening hole. A method of selecting or verifying the hole making technique by assessing the original fatigue quality of the fastening hole and checking compliance is given.