直升机桨叶不可见冲击损伤模型仿真  

Simulation of Helicopter Blade with Invisible Impact Damage

作　　者：奚佳凯 李建伟 XI Jiakai;LI Jianwei(China Helicopter Research and Development Institute, Jingdezhen 333001, China;Army Aviation Military Representative Office in Jiangdezhen, Jingdezhen 333002, China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]陆航驻景德镇地区军事代表室,江西景德镇333002

出　　处：《直升机技术》2018年第2期29-33,共5页Helicopter Technique

摘　　要：针对直升机桨叶在保管和使用过程中可能承受的低速冲击过程所导致的不可见损伤进行分析。使用有限元分析软件ABAQUS对桨叶复合材料进行建模分析。推导出复合材料在冲击作用下可能导致层间脱层现象,并且由于冲击损伤作用可能导致桨叶结构的应力分布产生变化,从而导致应力集中,最终影响到整体结构的强度。Based on finite element modeling of blade composites, this paper studied the helicopter blade of invisible damage under low speed impact. Through the analysis, the phenomenon of layered was found under low speed impact, eventually lead to the change of the stress distribution and the concentration of stress.

关 键 词：低速冲击 有限元建模 应力集中 

分 类 号：V214.41[航空宇航科学与技术—航空宇航推进理论与工程] V214.8