基于Abaqus二次开发的机身开口损伤容限分析  

DAMAGE TOLERANCE ANALYSIS FOR FUSELAGE OPENING BASED ON ABAQUS SECONDARY DEVELOPMENT

作　　者：詹福宇[1] 杨伟[1,2] 王生楠[1] 张志贤[2] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]成都飞机设计研究所,成都610041

出　　处：《机械强度》2014年第1期116-120,共5页Journal of Mechanical Strength

摘　　要：机身结构需要承受由飞行条件引起的机身剪力和弯曲力,以及由座舱压力引起的环向张力和纵向张力,开口损伤可能会逐渐形成裂纹并给飞机带来致命的影响。采用Python脚本语言对Abaqus进行二次开发,实现三维复合裂纹的参数化建模、自动扩展模拟和损伤容限评估,使整个裂纹扩展分析过程更加快速、方便和高效。然后对某运输机机身开口实际模型案例进行研究,预测裂纹扩展方向、输出裂纹扩展轨迹和应力强度因子,计算裂纹扩展寿命、剩余强度和检修周期。结果显示加强结构附近剩余强度可能发生不减反增的现象。为开口结构设计和检修提供参考及指导,具有一定工程意义。Fuselage structure needs to endure the shear and bending forc, es caused by fligh! conditions, as well circumferential tension and longitudinal tension caused by cabin pressure. The damage near the opening hole may gradually initiate cracks and cause fatal effect to the aircraft. A software was developed using Python scripting language in Abaqus. It performs the functions to build parametric model of 3D mixed-mode crack, then automatkally simulate crack growth and evaluate damage tolerance, hence makes the analysis of crack propagation much quicker, more convenient and effMent. Then a real case of certain conveyor fuselage opening model was studied. The crack propagation direction and lhe crack propagation path were predicted, stress intensity factors were output, the crack propagation life, residual strength and repair period were calculated. The results showed that the residual strength near the stiffened structure increased rather than decreased, which revealed a crack- arrest effect. The study provides a reference and guidance of some engineering significance for the design and repair of opening structure.

关 键 词：机身开口 复合裂纹 裂纹扩展 损伤容限 ABAQUS PYTHON 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程]