摘要
为了明确载荷对典型民用飞机的后机身加筋壁板结构设计的影响,建立低平尾式飞机后机身的有限元模型,计算分析了壁板的应力应变分布,计算分析了壁板不同区域的控制载荷工况、控制失效模式。通过对比不同失效模式各自所占的比例,证明后机身壁板结构的主要失效模式是屈曲以及最大应变准则。通过对比不同控制载荷工况各自所占的比例,选出后机身壁板结构的主要控制载荷工况。
In order to study the influences of the load on the design of aft fuselage stiffened structure of civil aircraft, the finite element model of low horizontal tail plane was established and analyzed. The stress and strain distribution, controlling load case and controlling failure mode of the different stiffened regions were calculated and analyzed. Comparison of the controlling failure mode proportion of different regions shows that buckling and maximum strain rule are the main failure modes of aft fuselage panel. By contrasting the controlling load case proportion in different regions, the main controlling load cases were gained. The result shows that aerodynamic load of horizontal tail has more influence on aft fuselage panel design than aerody- namic load of vertical tail.
出处
《沈阳航空航天大学学报》
2012年第3期60-63,共4页
Journal of Shenyang Aerospace University
关键词
后机身
控制失效模式
控制载荷工况
载荷
aft fuselage
controlling failure mode
controlling load case
load
