摘要
当前民用飞机的变弯度机翼主要通过机械式驱动实现机翼变形。在变弯度机翼后缘变形时,机翼蒙皮与驱动机构中驱动杆的相对位置关系会发生变化,往往导致驱动机构与蒙皮变形不协调问题。为满足变弯度机翼后缘变形设计要求,本文提出一种驱动机构与蒙皮的连接结构设计方案以实现变弯度机翼后缘变形协调。通过建立变弯度机翼后缘驱动机构运动模型,分析了变弯度机翼后缘在偏转过程中驱动机构与蒙皮连接点处机构点的运动特性,获得了机构点与蒙皮的相对位置关系。进而,通过研究蒙皮耳片开槽形式和开槽方法,对耳片及滑槽进行了设计。最后,通过对研制的变弯度机翼后缘试验样件开展变形和承载功能试验,验证了滑槽耳片设计方案可满足机翼变弯过程中的气动外形要求和承载能力要求。
Currently,the variable camber wings on civil aircraft are mainly morphed by mechanical drive.When the trailing edge of the variable camber wing morphs,there will be the change of the relative position relationship between the wing skin and the drive rod of the drive mechanism.This often leads to discordant deformation between the driving mechanism and the skin.To meet the morph design requirements of variable camber wing trailing edge,this paper proposed a design scheme of connecting structure between drive mechanism and skin to realize deformation coordination of the trailing edge.By establishing the motion model of the driving mechanism on the variable camber wing trailing edge,the motion characteristics of the mechanism points,the connection points between the driving mechanism and the skin during deflection of the trailing edge were analyzed,and the relative position relationship between the mechanism points and the skin was obtained.Then,the grooving form and method of lugs on skin were studied,and the design of chute lugs was carried on.Finally,the deformation and bearing capacity of the variable camber wing trailing edge prototype were tested,and the results showed that the chute lugs design scheme of the variable camber wing trailing edge can meet the requirements of aerodynamic shape and bearing capacity during bending of wing.
作者
董立君
薛景锋
李小飞
宋坤苓
Dong Lijun;Xue Jingfeng;Li Xiaofei;Song Kunling(Chinese Aeronautical Establishment,Beijing 100012,China)
出处
《航空科学技术》
2024年第12期8-15,共8页
Aeronautical Science & Technology
关键词
变弯度机翼
后缘
滑槽耳片
设计与验证
variable camber wing
trailing edge
chute lugs
design and validation
