直升机主桨轴颈损伤容限分析研究  

Damage Tolerance Analysis on Main Hub Mandril of Helicopter

作　　者：吴国冰 喻溅鉴[1] 王建[1] 吴艳霞[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》2014年第2期14-17,22,共5页Helicopter Technique

摘　　要：对直升机主桨轴颈进行了损伤容限分析,通过对桨叶连接耳片、阻尼器连接耳片和轴颈本体过渡段的损伤容限计算,给出了相应部位的裂纹扩展寿命、检查周期、检查手段和区域。进行损伤容限分析,给出检查周期,建立相应的检查手段,明确检查区域,可弥补安全寿命的不足,提高直升机的飞行安全性。The crack propagation life, inspection, inspecting method and the inspecting area of the blade connecting lug, damper connecting lug and the mandril transition part have been given by damage tolerance analysis to main hub mandril of the helicopter. The results indicated that it＇ s useful to complement the safe life method and improve the security of flight by building damage tolerance analysis system, giving the inspections, and confirming the inspecting methods of the area.

关 键 词：主桨轴颈 损伤容限 检查周期 

分 类 号：V215.56[航空宇航科学与技术—航空宇航推进理论与工程]