广义有限元法计算飞机开口裂纹应力强度因子  

Calculation of Stress Intensity Factor for Fuselage Opening's Crack Based on General Finite Element Method

作　　者：詹福宇[1] 王生楠[1] 张志贤[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2013年第1期49-53,共5页Advances in Aeronautical Science and Engineering

摘　　要：机身开口圆角损伤可能逐渐形成裂纹从而严重影响飞机使用安全,为此对圆角裂纹进行剩余强度估算显得十分重要。使用Williams位移场广义有限元法进行裂尖单元加强,并对裂尖区域应用放射形网格划分技术,编写广义有限元法的MATLAB程序,研究并计算飞机舱门开口圆角裂纹的应力强度因子。结果表明:在裂纹分析上,广义有限元法较常规有限元法具有更好的适应性和更高的精度。The damage of fuselage opening fillet may gradually be developed into a crack,which seriously influences the safety of aircraft,so it is necessary to estimate the residual strength of fillet crack.The General Finite Element Method（GFEM）of Williams displacement field is used to enrich the elements at crack tip.The radiated meshing technology is also applied at crack tip zone,and then the MATLAB program of GFEM is written to study and calculate the stress intensity factor（SIF）of fuselage opening＇s fillet crack.The results show that GFEM has a better flexibility and higher accuracy than Finite Element Method（FEM）in the analysis of crack.

关 键 词：广义有限元法 应力强度因子 机身开口裂纹 Williams位移场 

分 类 号：O346[理学—固体力学] V215[理学—力学]