某型飞机翼肋组件的有限元分析及改进设计

摘要

For the crack on a certain type of aircraft′s wing rib components, using Pro/E software, a three-dimensional model of wing rib components is established, the model is imported in ANSYS software to establish the finite element model.Using contact finite element method to simulate the mechanical behavior of rivet connection , bolt connection and contact of various components , the structure strength of aircraft′s wing rib components is analyzed under landing and flying conditions .The anal-ysis results show that, the aircraft′s wing rib components produce fatigue crack because the structure strength is insufficient. The improvement and comparison analysis for aircraft's wing rib components is carried out based on the analysis results, the improved design make the aircraft′s wing rib components have stronger structural fatigue strength and can effectively prevent fa-tigue crack.%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。