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飞机结构的失效很多都是由结构连接件孔边的开裂引起的,其结构疲劳寿命计算和损伤容限分析,必须计算孔边的旁路载荷和钉传载荷,通常可以通过查疲劳连接件手册,或通过解析法,但此类方法仅适用于两层且较为规则的连接。本论文从工程应用角度出发,引入刚度矩阵装配方法,该方法通过了几个经验公式来模拟紧固件的弹性模量,简化了计算紧固件弹性模量的环节,经实例计算对比,结果显示该方法可以满足工程计算的需要。
Many of the failure of aircraft structures are caused by the cracking of the hole edges of the structural connectors. The calculation of the fatigue life of the structure and the analysis of the damage tolerance must be done by calculating the bypass load and pinning load at the hole edge, usually by checking the Fatigue Connector Handbook , Or by parsing, but such methods apply only to two-tiered and more regular joins. In this paper, the rigid matrix assembly method is introduced from the perspective of engineering application. This method passes several empirical formulas to simulate the elastic modulus of fasteners and simplifies the calculation of the elastic modulus of fasteners. Comparing the examples, the results Show that this method can meet the needs of engineering calculations.