摘要
在全机有限元模型的基础上对机翼2～3墙间上壁板某处150mm裂纹型损伤进行修理前后的强度评估.给出了受损壁板修理后铆钉排数与残余过载的定量关系;比较了长桁受损后是否修理对飞机结构承载能力的影响.结论为战伤飞机快速评定提供了科学依据,也为飞机平时修理提供参考.
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.
出处
《力学与实践》
CSCD
北大核心
2008年第1期44-46,共3页
Mechanics in Engineering
关键词
整体壁扳
有限元
飞机
损伤修理
integral panel, finite element method （FEM）, aircraft, damage repair
