摘要
针对某型飞机机身蒙皮天线通过孔出现的裂纹,给出了具体的修理方案,结合结构几何特点和受载形式建立了修理结构的有限元细节模型,利用损伤容限分析流程及方法,进行了裂纹扩展分析和剩余强度分析,给出了开裂部位的裂纹扩展寿命和检查周期。分析结果显示,给定的修理方案满足损伤容限设计要求。该损伤容限分析流程及分析方法可以为此类结构修理的损伤容限评定提供参考。
Regarding to the crack emerged on the antenna hole structure of a aircraft fuselage skin, a certain repair plan was given. A detailed finite element model for the repaired structure was found on the basis of the geometry and load characteristics, and the crack growth analysis and the residual strength analysis were completed using the damage tolerance analysis flow and method, and the crack growth life and inspection periods were given. The results showed that the repair plan met the requirements of damage tolerance design. The damage tolerance analysis flow and method can provide reference for the kind of repaired structures.
出处
《航空科学技术》
2016年第7期21-25,共5页
Aeronautical Science & Technology
关键词
机身
蒙皮
结构修理
损伤容限
裂纹扩展寿命
检查周期
fuselage
skin
structure repair
damage tolerance analysis
crack growth life
inspection period
