飞机主承力结构细节分析  

The Detail Analysis for Primary Load-carrying Structure of the Aerocraft

作　　者：王想生[1] 赵彬[1] 李永刚 岳珠峰[1] 

机构地区：[1]西北工业大学工程力学系,陕西西安710072 [2]成都飞机工业有限责任公司技术中心,四川成都610092

出　　处：《飞机设计》2008年第6期12-17,共6页Aircraft Design

基　　金：国家自然科学基金项目(10472094);国家高技术研究发展专项(863)经费(2007AA04Z404)资助

摘　　要：工程上往往会遇到如飞机、轮船、汽车等大型结构,对这些大型结构进行有限元分析有时须同时考虑整体以及局部。对于大型结构采用较密的网格,这样会耗费大量时间、资源等,有时会导致计算不收敛;对于局部结构须划分较细的网格才能得到局部构件的细节应力。本文采用子结构法(超单元法)对机翼整体模型中的主承力构件梁进行网格细化,其中梁筋条与肋以及梁缘条与机翼蒙皮采用钉元(弹簧元)模拟多钉连接。在危险载荷工况下对梁进行强度校核和钉载分析,结果表明子结构法能很好地反映大型结构的整体以及细节应力分布,钉元法能很好地模拟机翼多钉连接。In the project we will often meet like the airplane, the steamboat, the automobile and so on large-scale structure. The whole analysis often be considered as well as the detail analysis for the large-scale structure during the finite element analysis. Using the dense grid regarding the large-scale structure, like this will cost the massive time, the resources and so on, sometimes will cause the computation not to convergence; the thin grid must he used to regard the partial structure which could obtain the partial eomponent＇s detail stress. This article uses the substructure law（ the super element method） to receive strength of primary load-carrying structure of the aerocraft through mesh refining, where the joint between the web and the rib of the primary load-carrying structure as well as the margin and the skin of the aerofoil were used as the nail element（ spring element）to simulate the multi- pinned connection. Carrying on the strength and bolt loading analysis under the dangerous load operat- ing mode to primary load-carrying structure of the aeroeraft, it is found that the substructure law can be successfully used to do the whole an detail analysis for the large-scale structure as well as the nail element method to simulation the multi-pinned connection of aerofoil.

关 键 词：超单元法 网格细化 弹簧元 多钉连接 

分 类 号：V214.41[航空宇航科学与技术—航空宇航推进理论与工程]