某复合材料主桨叶疲劳试验提前失效模式分析及改进  

Early Fatigue Failure Mode Analysis of XX CompositeMain Rotor Blade and Optimization

作　　者：孙涛[1] 刘伟光[1] 曾玖海[1] 贾良现[1] 

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2011年第2期60-64,共5页Helicopter Technique

摘　　要：首先介绍了某复合材料主桨叶疲劳试验提前破坏情况,并从结构设计、制造质量和试验方法三个方面进行分析,最终找出了试验载荷超过了桨叶过渡段后缘抗屈曲能力是此次疲劳试验提前失效的主要原因,另外摆振刚度突变和模压桨叶质量差是导致在1000剖面附近开胶的重要原因。在第二次疲劳试验时,通过改进桨叶结构和制造工艺,调整试验载荷,最终获得了疲劳试验验证。Early fatigue failure of XX composite main rotor blade was introduced,and we had analyzed the failure mode by structure design methods,quality of manufacture and test methods in this paper.In conclusion,test load exceeded flexure load of main rotor blade is the main reason and the large change of lead-lag stiffness and the low quality of blade are key reason.Some advices had been taken to improve the main rotor blade.Finally the second fatigue test of validated the optimization of structure design,quality of main rotor blade and the test load.

关 键 词：主桨叶 失效模式 分析 改进 

分 类 号：V21[航空宇航科学与技术—航空宇航推进理论与工程]