带裂孔的直升机尾传动轴屈曲强度仿真与试验研究  

Numerical Simulation and Experimental Study on Buckling Strength of Helicopter Tail Drive Shafts with Crack Holes

作　　者：乔纪祥 叶飞 赵思波 李坚 Qiao Ji-xiang;Ye Fei;Zhao Si-bo;Li Jian(China Aero-Engine Development Institute of Hunan Power Mechanical Research Institute,Hunan Zhuzhou 412000;The Army Armament Department)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412000 [2]陆军装备部某部

出　　处：《内燃机与配件》2025年第4期127-130,共4页Internal Combustion Engine & Parts

摘　　要：直升机传动系统尾传动轴存在屈曲失稳的现象且有被击穿的风险,击穿后屈曲失稳的可能性更大,影响飞行器安全。基于非线性屈曲理论与有限元仿真技术,开展带裂孔的直升机尾传动轴非线性屈曲分析并进行试验验证,分别获得存在不同入射角、入射偏置的贯穿损伤情况下,尾传动轴非线性屈曲模式和屈曲临界载荷,并与线性屈曲结构进行对比。发现随着入射角和入射偏置的增大,传动轴的临界屈曲载荷会降低,且在切边损伤下发生剧烈下降。The tail drive shaft within a helicopter's transmission system is prone to buckling instability and poses a risk of perforation.Once perforated,the structure becomes more susceptible to buckling instability,thereby compromising flight safety.This study employs nonlinear buckling theory in conjunction with finite element analysis(FEA)to investigate the nonlinear buckling behavior of helicopter tail drive shafts containing crack holes.Experimental validation was performed to corroborate the simulation results.The investigation covers scenarios with varying impact angles and offsets for through-thickness damage,examining the resulting nonlinear buckling modes and critical buckling loads.These findings are compared against those from linear buckling analyses.It was observed that an increase in both impact angle and offset leads to a reduction in the critical buckling load of the drive shaft.Notably,there is a sharp decline in the critical buckling load when the incident path passes through the radius of the shaft tube,creating a notch or groove along the edge.

关 键 词：扭转屈曲 有限元仿真 尾传动轴 非线性屈曲分析 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]