摘要
直升机机身蒙皮为薄面板蜂窝夹层结构,蜂窝夹层结构在较低能量的冲击下就会产生损伤,给飞行带来风险。本文采用有限元方法,对直升机机身蒙皮的冲击进行了仿真模拟。基于ABAQUS建立薄面板蜂窝夹层结构的有限元仿真模型,由于复合材料面板冲击过程中发生渐进失效,因此开发VUMAT用户子程序,自定义其本构关系,采用Yen失效准则模拟双向编织复合材料面板损伤起始和损伤扩展方式,并根据损伤形式对损伤单元进行刚度折减,以实现材料性能的退化,同时蜂窝芯体采用等效弹塑性模型,并引入Cohesive单元模拟胶层。冲击能量较低时,冲击损伤表现为面板凹坑、少量纤维断裂、基体损伤及分层。对比仿真与试验,两者具有较好的一致性,由此表明有限元仿真能够有效分析蜂窝的冲击损伤,为直升机机身蒙皮的抗冲击设计提供参考。
The helicopter fuselage skin is a thin panel honeycomb sandwich structure,and the honeycomb sandwich structure can be damaged at a lower energy impact,which poses a risk to flight.In this paper;a finite element method is used to simulate the impact of helicopter fuselage skin.Based on ABAQUS to establish the finite element simulation model of thin panel honeycomb sandwich structure,since progressive failure occurs during the impact of composite panel,VUMAT user subroutine is developed to customize its intrinsic structure relationship,and Yen failure criterion is used to simulate the damage initiation and damage expansion mode of bi-directional woven composite panel,and the stiffness of damage cells are discounted according to the damage form to achieve material At the same time,the honeycomb core adopts the equivalent elastic-plastic model and introduces the Cohesive unit to simulate the adhesive layer.Comparing the simulation and test,the two are in good agreement,which shows that the finite element simulation can effectively analyze the impact damage of honeycomb and provide reference for the impact resistance design of helicopter fuselage skin.
作者
宋畅
岳巍
Song Chang;Yue Wei(China Helicopter Research and Development Iinstitute,Jingdezhen Jiangxi 333001)
出处
《中国科技纵横》
2022年第4期91-93,96,共4页
China Science & Technology Overview
关键词
薄面板蜂窝夹层结构
冲击损伤
失效准则
有限元
thin panel honeycomb sandwich structure
impact damage
failure criterion
finite element
