%0 Journal Article
%T DAMAGE REPAIR ANALYSIS FOR INTEGRAL WING PANEL OF AN AIRCRAFT<br>某飞机机翼整体壁板损伤修理的有限元分析
%A LI Yan
%A YU Kejie
%A <br>李艳
%J 力学与实践
%D 2008
%I 
%X On the basis of the finite element model of a whole aircraft, the paper simulates a crack with a length of 150 mm in a place between No.2 and No.3 walls of the upper wing panel before and after it is repaired. The results give a quantitative relationship between rivet rows and residual load factor, and the influences of the damaged stringer, before and after it is repaired, on the force-bearing ability of aircraft structure are compared. The results can be used in a rapid assessment of a battle-damaged aircraft repair and as a reference for the usual repair of aircraft.
%K 整体壁板
%K 有限元
%K 飞机
%K 损伤修理
%U http://www.alljournals.cn/get_abstract_url.aspx?pcid=6E709DC38FA1D09A4B578DD0906875B5B44D4D294832BB8E&cid=5D344E2AD54D14F8&jid=0BF5C9FB031A532ED0A6D99DC4F6181A&aid=366116A075968359D791C61BBA61CC69&yid=67289AFF6305E306&vid=340AC2BF8E7AB4FD&iid=CA4FD0336C81A37A&sid=1AE5323881A5ECDC&eid=D997634CFE9B6321&journal_id=1000-0879&journal_name=力学与实践&referenced_num=0&reference_num=6