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针对某型飞机翼肋组件裂纹问题,利用Pro/E软件对翼肋组件进行三维建模,将其导入ANSYS软件中建立了有限元模型。采用接触有限元方法模拟铆钉联接、螺栓联接及各构件间接触的力学特征,对着陆和飞行两种工况下翼肋组件的结构强度进行了分析。分析结果表明,飞行工况中,翼肋组件结构强度不足导致了疲劳裂纹产生。根据分析结果对翼肋组件进行了改进和比较分析,改进设计后的翼肋组件结构疲劳强度得到了较大提高,可有效预防疲劳裂纹产生。
Aiming at the crack problem of a certain type of aircraft wing rib assembly, the rib assembly is modeled by Pro / E software and imported into ANSYS software to establish the finite element model. The contact finite element method is used to simulate the mechanical characteristics of the rivet joint, the bolt joint and the contact between the components, and the structural strength of the ribbed assembly under both the landing and the flying conditions is analyzed. The results of the analysis show that the fatigue strength of the rib assembly is not sufficient in the flight condition. Based on the analysis result, the ribbed components are improved and compared. The fatigue strength of the ribbed components with improved design has been greatly improved, which can effectively prevent the occurrence of fatigue cracks.