面向飞机数字化装配的工艺接头承载分析  

Loading analysis of joint part for aircraft digital assembly

作　　者：盖宇春[1] 蒋君侠[1] 曲巍葳[1] 柯映林[1] 黄浦缙[1] 

机构地区：[1]浙江大学机械工程学系,浙江杭州310027

出　　处：《浙江大学学报（工学版）》2012年第10期1737-1743,1783,共8页Journal of Zhejiang University：Engineering Science

基　　金：国家自然科学基金资助项目(50905161);浙江省自然科学基金资助项目(Y1110339)

摘　　要：针对大飞机数字化装配工艺需求,设计一种工艺接头用于定位器与机身之间的过渡连接.为了保证飞机装配质量,对机身工艺接头的承载能力和机身受力状态进行有限元建模和分析.采用带耦合约束的梁单元模拟螺栓受力,分析机身与螺栓的载荷分布情况.分析结果表明,机身与工艺接头之间的接触应力较小,机身隔框上的最大应力只有螺栓孔区域应力的1/3.各螺栓的受载情况差别较大,且有较大的轴向载荷作用.分析工艺接头的结构特征和设计参数对螺栓载荷分布的影响,总结了一些螺栓载荷分布规律:布置在隔框周向边缘的螺栓径向载荷较大,在加载位置附近的螺栓轴向载荷较大;增加机身连接面板的厚度能够使螺栓的受载均匀化,增加螺栓数量可以减小螺栓的径向载荷,对轴向载荷的影响不显著.The fuselage joint was designed for the connection between fuselage and positioners according to the processes requirement of large aircraft digital assembly. The finite element model was constructed to investigate the fuselage joint supporting capacity and the fuselage loading status in order to guarantee the aircraft assembly quality. The load distribution on fuselage and bolts was analyzed with coupling beam bolt mode. Results indicated that the contact stress between fuselage and fuselage joint was neglectable, and the maximal stress on frame was 1/3 of the stress on bolt hole. There was great difference in bolt load, and large axial load was observed. The effect of joint parameter on bolt load distribution was investigated. Results showed that bolts＇ radial load was greater at the circumferential edge of frame, and bolts＇ axial load was relatively large near the loading location. Increasing the thickness of the joint panel can make the load of bolt homogenized. Increasing the number of bolts can reduce the bolts＇ radial load, while the bolts＇ axial load was not significantly changed.

关 键 词：机身 机身工艺接头 有限元 螺栓 载荷分布 

分 类 号：V264.2[航空宇航科学与技术—航空宇航制造工程] TH122[机械工程—机械设计及理论]