摘要
翼身融合中央机体由于承受舱内压力载荷和较高的机翼弯曲载荷,而这些载荷会导致严重的非线性应力特性,并引起较大的结构变形和很高的应力集中,同时由于发动机后置的影响,增加了翼身融合机体的航向弯矩与低头力矩,针对这个问题,本文重点考虑材料和结构设计这2个方面,对翼身融合飞机中央机体结构采用高强度复合材料和纵墙加强的方式进行结构设计,并对设计的机体结构进行分析,得到中央机体的刚度和强度。
The fuselage part of the wing-body must bear the pressure load,bending loads,which will lead to inestimable nonlinear stress characteristics,may cause severe deformation and high stress concentration.At the same time,due to the influence of the rear position of the engine,the heading bending moment and low head moment of the wing-body fusion body are increased.In order to solve this problem,this paper starts from two aspects of material and structure design.The structural design of the central body of the wing-body fusion aircraft is carried out by means of high-strength composite materials and longitudinal wall reinforcement.The designed body structure is analyzed,and the stiffness and strength of the central body are obtained.
作者
李倩
聂小华
田瑞
Li Qian;Nie Xiaohua;Tian Rui(Aircraft Strength Research Institute of China,Xi’an Shaanxi 710065,China)
出处
《工程与试验》
2020年第1期39-42,共4页
Engineering and Test
