蜂窝夹层边缘斜削区强度仿真分析  

Strength simulation analysis of the edge ramp area of honeycomb sandwich

作　　者：门坤发 黄汉超[2] 林长亮 韩刘 MEN Kunfa;HUANG Hanchao;LIN Changliang;HAN Liu(AVIC Harbin Aircraf Industry Group Co.Ltd.,Harbin 15906,China;Army Aviation Institute,Beijing 101123,China)

机构地区：[1]哈尔滨飞机工业集团有限责任公司,哈尔滨150066 [2]陆军航空兵学院航空机械工程系,北京101123

出　　处：《民用飞机设计与研究》2022年第4期8-12,共5页Civil Aircraft Design & Research

摘　　要：蜂窝夹层在航空器结构尤其是直升机结构中有着广泛的应用,其中边缘闭合是夹层结构设计的特有问题,采用斜削结构过渡并与其它结构实现连接是一种典型的形式,考虑到蜂窝夹层结构在成型中斜削区施加压力的不均匀性,在斜削区与蜂窝芯子通过膨胀胶膜胶接从而避免结构脱粘,但在高温影响下膨胀胶膜的力学性能出现降低,导致蜂窝夹层边缘斜削区位置粘接强度受到影响,从而影响到整个蜂窝夹层结构边缘的传力,利用静强度分析了在常温使用条件下斜削区膨胀胶膜完全起作用下蜂窝夹层边缘的应力分布,考虑到胶膜在120℃使用环境下管剪切性能降低的情况,利用热力耦合的方法分析了在120℃使用环境下蜂窝夹层边缘的应力情况,计算结果表明在高温状态膨胀胶膜不起作用的情况下蜂窝夹层结构边缘斜削区仍满足强度要求。The honeycomb sandwich is widely used in the aircraft structure,especially in helicopter structure.The edge closure is a specific problem for this structure.The ramp areas of the sandwich edge is a typical form to transition and link with other structure.The sandwich ramps area usually used the intumescent adhesive bonding the honeycomb due to the curing pressure was no uniform during the molding process,and its mechanical properties was decreased gradually with the rise of temperature.As a result,the bonding strength at the ramp area of honeycomb sandwich was affected,which affected the force transmission at the edge of the entire honeycomb sandwich structure.The stress distribution at the edge of honeycomb sandwich under the full action of the intumescent adhesive in the ramp area at normal temperature was analyzed by the static strength.Considering that the intumescent adhesive tube shear performance was reduced at 120℃,the stress at the edge of honeycomb sandwich under 120℃environment was analyzed by using thermo-mechanical coupling method.The calculation results show that the ramp area of honeycomb sandwich structure still meets the strength requirement under the condition of high temperature without the effect of intumescent adhesive.

关 键 词：强度仿真 斜削区 膨胀胶膜 热力耦合 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程] V216