摘要
以某型直升机铝面板/铝蜂窝夹层结构为对象,进行承压能力研究,得到此结构在大垂向均布载荷下面板的载荷-应变试验曲线、主要破坏模式和极限承载载荷。同时,利用有限元分析软件Patran/Nastran对该结构进行有限元建模和分析并与试验结果进行对比分析,结果表明采用非线性三维有限元分析模型可以快速准确地为该类结构的分析设计提供参考依据。
The bearing capacity of an aluminum paneL/aluminum honeycomb sandwich structure of helicopter under large vertical load was researched. Its load - strain curve, failure mode and ulti- mate load were gained while vertical uniform pressure was loaded. The structure was modeled and analyzed by finite element method using Patran/Nastran. The comparison with experiments showed that nonlinear three - dimensional finite element model could provide accurate and fast references for design and analysis of this kind of structures.
出处
《直升机技术》
2018年第1期31-34,40,共5页
Helicopter Technique
关键词
蜂窝夹层结构
承压
试验
有限元方法
honeycomb sandwich
pressure
test
finite element method
