摘要
研究应力场强法在飞机结构抗疲劳设计中的应用;论述飞机结构的典型细节模型;提出了对应于细节模型的应力场强法的疲劳寿命分析方法和相应的疲劳模拟试验件的设计方法。据此对一个飞机结构危险部位作了疲劳寿命分析和试验验证。分析和试验结果表明:提出的方法是合理的。
This paper studies application of stress field intensity method in fatigue resistant design of aircraft structure;describes typical detail model of aircraft structure;and presents fatigue life analysis method corresponding to stress field intensity method and design method relating to fatigue simulaiton test piece.The analysis of fatigue life for one critical position of aircraft structure and test verification are carried out accordingly.The analysis and test result prove the present method is reasonable.
出处
《洪都科技》
2001年第4期14-18,共5页
Hongdu Science and Technology
关键词
疲劳寿命
应力场强法
连接件
飞机结构
Fatigue life Stress field intensity method Connecting part Aircraft structure
