摘要
根据复合材料层压板及夹层结构设计原则提出了某飞机机尾罩复合材料设计方案,结合复合材料强度计算方法进行有限元分析及强度校核。分析结果表明:在满足静强度的前提下,与金属机尾罩相比,复合材料机尾罩重量减少28.4%。
The design scheme of tail fairing of an aircraft is provided as per the design principles of composite material laminated plate and sandwich structure, besides, the finite element and strength check are performed, besides, the finite element and strength check are performed as per the strength calculation method of composite material. The analyzed rcsuh shows that the weight of composite material tail fairing is reduced 28.4% compared to that of metal one, when the static strength requirements is fulfilled.
出处
《教练机》
2015年第1期65-68,共4页
Trainer
关键词
复合材料
层压板
夹层结构
有限元法
composite material
laminates
sandwich structure
finite element method
