The invention belongs to the field of aircraft assembly, and discloses an airplane spoiler mounting method. The installation coordination between main joints and auxiliary joints is realized by takingan intersection point hole of the spoiler suspension main joints and auxiliary joints as a benchmark; the position of a beam plane is controlled; a joint intersection conformal tool is adopted to ensure the coaxiality of joint intersection points and the notch gap, and deformation of spoiler mounting intersection points is controlled; the gap coordination benchmark between the front edge of the spoiler and a butt joint structure is determined by additionally arranging a spoiler simulation piece, the aircraft wing spoiler meeting the design requirement is mounted, and the purposes of the opening angle and the motion performance requirement of the spoiler are achieved.
本发明属于飞机装配领域,公开了一种飞机扰流板安装方法,通过扰流板悬挂主接头、辅助接头交点孔为基准,实现了主接头和辅助接头之间的安装协调,并对梁平面的位置进行了控制,采用接头交点保形工装,保证了接头交点同轴度及槽口间隙,控制了扰流板安装交点的变形,并通过增加扰流板模拟件,确定了扰流板前缘与对接结构之间的间隙协调基准,安装出满足设计要求的飞机机翼扰流板,实现了扰流板开启角度和运动性能要求的目的。
Airplane spoiler mounting method
一种飞机扰流板安装方法
2020-10-09
Patent
Electronic Resource
Chinese
Airplane spoiler manufacturing method, airplane spoiler and airplane
European Patent Office | 2015
|