预腐蚀铝基复合材料疲劳寿命的预测方法  

Fatigue Life Prediction Method of Pre-Corroded Aluminum Matrix Composite

作　　者：陈亚萍[1] 曾本银[1] 喻溅鉴[1] 袁璐 CHEN Yaping;ZENG Benyin;YU Jianjian;YUAN Lu(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Shanghai Aeronautical Materials&Structures Testing Co.,Ltd.,Shanghai 200000,China)

机构地区：[1]中国直升机设计研究所,景德镇333001 [2]上海航空材料结构检测股份有限公司,上海200000

出　　处：《腐蚀与防护》2021年第1期36-41,共6页Corrosion & Protection

摘　　要：根据铝基复合材料(AMC)的腐蚀特征研究结果,采用基于疲劳缺口系数表征和基于断裂力学等效应力强度因子表征的两种方法建模,对铝基复合材料结构预腐蚀后的疲劳寿命进行预测,并与试验结果进行对比验证。结果表明:基于疲劳缺口系数表征的预测结果在高周疲劳段与试验值更接近,可用于确定直升机高周疲劳结构件腐蚀缺陷容限尺寸和腐蚀缺陷检查周期等;基于断裂力学等效应力强度因子表征的预测结果在低周疲劳段与试验值更接近,可用于指导直升机低周疲劳结构损伤容限设计。Through the research of corrosion characteristic of aluminum matrix composite(AMC),the models to forecast the pre-corrosion fatigue life of AMC were built based on fatigue indentation factor and fracture mechanics equivalent stress intensity factor,and the forecast results were compared with the test results.The comparison results show that the result forecasted by first model was more close to the test result in high-cycle fatigue and could be used to ascertain the corrosion defect tolerance size and inspection intervals for high-cycle fatigue structure of helicopter.The result forecasted by second model was more close to the test result in low-cycle fatigue and could be used to guide the damage tolerance design for low-cycle fatigue structure of helicopter.

关 键 词：直升机 复合材料 预腐蚀 疲劳寿命预测 方法 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程]