摘要
以飞机机身典型部位复合材料与Z型长桁螺栓连接为研究对象,采用Python脚本语言编程,在ABAQUS平台建立了6种紧固长度有限元模型,模拟飞机在高空低温的飞行环境,得到了混合结构的应力、应变分布规律。数值仿真结果表明:铝梁顶部应变结果呈现中间高、两边低的现象,紧固螺栓应变结果则呈现出相反的趋势;末端紧固件承受的剪切载荷最大,而中心的紧固件剪切载荷最小;该温度场结果与已有文献的试验测试结果误差在3℃以内,对复合材料与金属混合结构的设计具有一定意义。
The multi-bolt connection of composite parts of aircraft fuselage typical parts and Z-shaped aluminum alloy long rafts is studied.By using the Python scripting language program,six finite element models of fastening lengths are established on the ABAQUS platform to simulate the low temperature of the aircraft at high altitudes,the stress and strain distribution laws of the hybrid structure are obtained.Numerical simulation results show that the strain at the top of the aluminum beam is high in the middle and low on both sides.The fastening bolts show the opposite trend.The end fasteners bear the highest shear load,while the central fasteners have the smallest shear loadings.The relative error between the temperature field and the reference test results is 3℃,which has certain significance for the composite structure design of composite materials.
作者
邓文亮
成竹
唐虎
Deng Wenliang;Cheng Zhu;Tang Hu(Aircraft Strength Research Institute of China,710065,Xi’an,China;School of Aeronautic Science and Engineering,Beihang University,100083,Beijing,China)
出处
《应用力学学报》
CAS
CSCD
北大核心
2020年第2期550-557,I0006,共9页
Chinese Journal of Applied Mechanics
基金
民机课题“极端气候条件下的民机结构与机构适用性分析与验证技术研究”。
关键词
复合材料
螺栓连接
混合结构
温度场
应力场
二次开发
composite materials
bolted
hybrid structure
temperature field
stress field
secondary development
