摘要
以现有的耐久性分析模型和损伤容限分析模型为基础,综合研究裂纹萌生和扩展的全过程,建立了飞机结构耐久性/损伤容限综合分析模型,并且通过一个具体的算例证明了模型的可行性。该模型兼顾了结构的寿命、安全以及检修一体化的要求,可用于对飞机结构进行综合设计与分析。
By studying the total process of crack initiation and crack growth, a new model of flight structural durability and damage tolerance analysis by synthesis is presented. It is based on the existing durability analysis method PFMA and the probability damage tolerance analysis model, so it can be used to analyze the flight structural performance of durability and damage tolerance at the same time. It is propitious to analysis and optimizing the design of flight structures. Finally, a calculation example is presented to validate the feasibility of this new model.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2004年第2期133-136,共4页
Acta Aeronautica et Astronautica Sinica
关键词
飞机结构
耐久性
损伤容限
分析模型
Analysis
Crack initiation
Durability
Failure (mechanical)
Structures (built objects)
