紧固孔原始疲劳质量控制与制孔技术研究

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９５％要求的当量初始裂纹尺寸ａｉ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。

RESEARCH ON FASTENER HOLE INITIAL FATIGUE QUALITY AND MANUFACTER TECHNIQUE

The initial fatigue quality of aircraft structure fastener holes that has an important effect to aircraft structure durability and safety is studied. The initial fatigUe quality is defined by the equivalent initial crick size al, which has 95% confidence and 95% reliability. The relationships between manufacture hole technical and the initial fatigUe quality of fastener holes is presented. The quantitative analysis method of initial fatigue quality based on stochastic crack growth method and deterministic crack growth approaches is giv en. The new method have several practical applications for metallic alrframes, including: (l) ensuring aircraft damage tolerance and/or durability design requirement under different manufacture hole technical, (2) structural reliability based design under different manufac ture hole technical, and (3) reliability centered maintenance.