直升机风挡透明件弯曲性能分析  

Analysis of Bending Performance of Helicopter’s Windshield Transparent Part

作　　者：朱慧玲 王海涛 杨磊[1] ZHU Huiling;WANG Haitao;YANG Lei(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Nany Representative Office in Nancnang,Nanchang 330000,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001 [2]海装驻南昌地区军事代表室,江西南昌330000

出　　处：《直升机技术》2022年第4期27-30,共4页Helicopter Technique

摘　　要：直升机飞行过程中,前机身的风挡玻璃不可避免地要承受载荷。针对直升机风挡透明件,基于有限元法建立数学模型并求解Von-Mises应力和变形情况;采用四点弯曲法和材料试验机进行弯曲试验,得到国产及进口两种材料风挡透明件的破坏载荷,并进一步分析加载速率对弯曲性能的影响。结果表明:最大Von-Mises应力、最大变形均位于加载辊间,弯曲试验中试件断裂源位置包含加载辊间、加载辊外侧两种形式;最大弯曲变形相同的条件下,最大载荷随加载速率的增大而增大,增长幅度较小。During flight of helicopter,the windshield glass of the front fuselage inevitably bears load.For the windshield transparent part of helicopter,established the mathematical mode and solved the Von-Mises stress and deformation conditions based on the finite element method.The four-point bending method and material testing machine were used to carry out the bending test to obtain the breaking load of the windshield transparent parts made of domestic and imported materials.Further,analyzed the influence of the loading rate on the bending performance.The results showed that,the maximum Von-Mises stress and the maximum deformation were located between the two loading rods.In the bending test,the fracture position included between the two loading rods and the outside of the loading rod.Under the same maximum deformation condition,the maximum load increased with the increase of the loading rate and the increase was small.

关 键 词：风挡透明件 四点弯曲法 弯曲性能 加载速率 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]