Please wait a minute...
浙江大学学报(工学版)
J4  2012, Vol. 46 Issue (10): 1737-1743    DOI: 10.3785/j.issn.1008-973X.2012.10.002
机械与能源工程     
面向飞机数字化装配的工艺接头承载分析
盖宇春, 蒋君侠, 曲巍葳, 柯映林, 黄浦缙
浙江大学 机械工程学系,浙江 杭州 310027
Loading analysis of joint part for aircraft digital assembly
GAI Yu-chun, JIANG Jun-xia, QU Wei-wei, KE Ying-lin, HUANG Pu-jin
Department of Mechanical Engineering, Zhejiang University, Hangzhou 310027, China
 全文: PDF  HTML
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.
Abstract:

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.
出版日期: 2012-10-01
:  V 264.2  
基金资助:

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).
通讯作者: 曲巍葳,女, 助理研究员.     E-mail: qwwwwl@163.com
作者简介: 盖宇春(1981—),男,博士生.从事先进制造技术与装备、飞机数字化装配的研究.E-mail: gyccc@sohu.com
服务　　
把本文推荐给朋友
加入引用管理器
E-mail Alert
RSS
作者相关文章　　

引用本文:

盖宇春, 蒋君侠, 曲巍葳, 柯映林, 黄浦缙. 面向飞机数字化装配的工艺接头承载分析[J]. J4, 2012, 46(10): 1737-1743.

GAI Yu-chun, JIANG Jun-xia, QU Wei-wei, KE Ying-lin, HUANG Pu-jin. Loading analysis of joint part for aircraft digital assembly. J4, 2012, 46(10): 1737-1743.

链接本文:

http://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2012.10.002    或    http://www.zjujournals.com/eng/CN/Y2012/V46/I10/1737

［1］ 邹冀华,刘志存,范玉青.大型飞机部件数字化对接装配技术研究［J］.计算机集成制造系统,2007, 13(7)： 1367-1373.
ZOU Jihua, LIU Zhicun, FAN Yuqing. Largesize airplane parts digital assembly technology ［J］. Computer Integrated Manufacturing Systems, 2007, 13(7): 1367-1373.

［2］ 郭恩明.国外飞机柔性装配技术［J］.航空制造技术,2005(9): 28-32.
GUO Enming. Flexible assembling technology for overseas aircraft ［J］. Aeronautical Manufacturing Technology, 2005(9): 2832.
［3］ 范玉青.飞机数字化装配技术综述［J］.航空制造技术,2006(10): 42-48.
FAN Yuqing. Digital assembly for aircraft ［J］. Aeronautical Manufacturing Technology, 2006(10): 42-48.
［4］ 牛春匀.实用飞机结构工程设计［M］.北京：航空工业出版社,2008: 477-478.
［5］ 李曙林.飞机与发动机强度［M］. 北京：国防工艺出版社, 2007: 61-67.
［6］ 王志瑾,姚卫星.飞机结构设计［M］.北京：国防工业出版社,2007: 139-143.
［7］  TAE S K, HITOSHI K. Finite element modeling of bolted connections in thinwalled stainless steel plates under static shear ［J］. ThinWalled Structures, 2007, 45(4): 407-421.
［8］  HONG K, YANG J K, LEE S K. Momentrotation behavior of double angle connections subjected to shear load ［J］. Engineering Structures, 2002, 24(1): 125-132.
［9］ MAGGI Y I, GONCALVES R M, LEON R T, et al. Parametric analysis of steel bolted end plate connections using finite element modeling ［J］. Journal of Constructional Steel Research, 2005, 61(5): 689-708.
［10］ 赵美英,阎国良,顾亦磊,等.复合材料层板钉群连接载荷分配计算方法研究［J］.航空计算技术,2006,36(3): 97-101.
ZHAO Meiying, YAN Guoliang, GU Yilei, et al. Design of computation methods of the load distribution in composite fastener group joints ［J］. Aeronautical Computing Technique, 2006, 36(3): 97-101.
［11］ 赵群,丁运亮,金海波.结构刚度对翼根螺栓组载荷分布的影响［J］.航空学报,2008,29(4): 931-936.
ZHAO Qun, DING Yunliang, JIN Haibo. Effects of structure stiffnesses on the load distribution of bolt group at wing root ［J］. Acta Aeronautica et Astronautica Sinica, 2008, 29(4): 931-936.
［12］ BONI L, FANTERIA D. Development of analytical methods for fuselage design: validation by means of finite element analyses ［J］. Proceeding of Institution of Mechanical Engineers PartG: Journal of Aerospace Engineering, 2004, 218(5): 315-327.
［13］ BONI L, FANTERIA D. Finiteelementbased assessment of analytical methods for the design of fuselage frames ［J］. Proceeding of Institution of Mechanical Engineers PartG: Journal of Aerospace Engineering, 2006, 220(5): 387-398.
［14］ 庄茁,廖剑松,岑松,等.基于ABAQUS的有限元分析和应用［M］.北京：清华大学出版社, 2009: 62-69.
［15］ JEONG K, JOO C Y, BEON S K. Finite element analysis and modeling of structure with bolted joints ［J］. Applied Mathematical Modeling, 2007, 31(5): 895-911.
[1] 盖宇春, 朱伟东, 柯映林. 大型飞机总装配中支撑点设计分析技术[J]. J4, 2013, 47(12): 2176-2183.