摘要
机翼蒙皮处的多部位损伤危及结构的完整性,随着裂纹的扩展,多部位损伤结构裂纹的相互作用增强,给飞机的安全和寿命带来极大考验.为研究裂纹分布模式及结构参数对裂间相互作用的影响规律,开展基于FRANC3D对多部位损伤结构裂纹尖端相互影响因子的仿真研究.通过对比共线双侧等长疲劳裂纹的实验与仿真分析结果,验证了该方法的有效性;再对不同模式的共线多裂纹的疲劳裂纹扩展进行模拟,分析了各种模式下裂纹扩展的影响规律,对多部位损伤结构裂纹扩展分析和损伤容限设计具有一定意义和工程应用价值.
The multiple site damage at the wing skin poses a threat to the integrity of the structure.As cracks propagate,the interaction between the multi site damage and structural cracks intensifies,posing a great challenge to the safety and lifespan of the aircraft.In order to study the influence of crack distribution patterns and structural parameters on the interaction between cracks,this paper carried out a simulation study based on FRANC3D on the interaction factor of crack tips of Multiple Site Damage structures.By comparing the experimental and simulation analysis results of collinear bilateral isometric fatigue cracks,the effectiveness of the proposed method is verified.Then,the fatigue crack propagation under different modes of collinear multi-crack and the influence law of crack propagation under various models is analyzed,which is of significance and engineering application value for the analysis of multi-site damage structure crack propagation and damage tolerance design.
作者
施金湘奕
赵晋芳
侯婧
柳思畅
SHIJIN Xiangyi;ZHAO Jinfang;HOU Jing;LIU Sichang(College of Civil Aviation,Shenyang Aerospace University,Shenyang,Liaoning Province,110136 China;Key Laboratory of Fundamental Science for National Defense of Aeronautical Digital Manufacturing Process,Shenyang Aerospace University,Shenyang,Liaoning Province,110136 China)
出处
《大众科学》
2024年第17期38-41,共4页
China Public Science
基金
沈阳航空航天大学国防重点实验室开放基金(项目编号:SHSYS202208)
沈阳航空航天大学大学生创新创业训练计划项目(项目编号:X202310143162)。
关键词
多部位损伤
裂纹分布
有限元分析
相互影响因子
裂纹扩展寿命
Multiple site damages
Crack distribution
Finite element analysis
Interaction factor
Crack propagation life
作者简介
施金湘奕(2003-),女,本科,研究方向为飞行器质量与可靠性;侯婧(2003-),女,本科,研究方向为飞行器质量与可靠性;通信作者:赵晋芳(1981-),女,博士,副教授,研究方向为结构强度与可靠性,E-mail:1910142867@qq.com。
