The invention discloses a damping composite aircraft control surface structure which comprises a first reinforcing rib, a second reinforcing rib, a third reinforcing rib, a variable-thickness skin, a damper, a rudder shaft and a surrounding plate. The first reinforcing rib, the second reinforcing rib and the third reinforcing rib are all connected with the coaming and connected to the rudder shaft, the first reinforcing rib points to the front edge of the rudder surface structure, the second reinforcing rib is arranged in the spanwise direction, the third reinforcing rib points to the wingtip, and a reinforcing rib framework of a tree-shaped structure is formed; the variable-thickness skins are arranged up and down and connected with the coaming, the first reinforcing rib, the second reinforcing rib, the third reinforcing rib and the dampers are surrounded to form a sandwich structure, and the dampers are embedded among the first reinforcing rib, the second reinforcing rib and the variable-thickness skins. The invention relates to the technical field of aircraft structures, and provides a novel aircraft control surface structure.
本发明公开了一种阻尼复合飞行器舵面结构,包括第一加强筋、第二加强筋、第三加强筋、变厚度蒙皮、阻尼器、舵轴和围板;第一加强筋、第二加强筋、第三加强筋均与围板相连并连接在舵轴上,其中,第一加强筋指向舵面结构前缘,第二加强筋沿展向布置,第三加强筋指向翼尖,形成呈树状结构的加强筋骨架;变厚度蒙皮上下布置并与围板相连,将第一加强筋、第二加强筋、第三加强筋及若干个阻尼器包围,形成三明治结构,其中,若干个阻尼器嵌装在第一加强筋、第二加强筋和变厚度蒙皮之间。本发明涉及飞行器结构技术领域,提供一种新型的飞行器舵面结构。
Damping composite aircraft control surface structure
阻尼复合飞行器舵面结构
2025-01-10
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Automatic control for damping large aircraft elastic vibrations
Engineering Index Backfile | 1968
|Electrorheological damping aircraft nose landing gear and aircraft
European Patent Office | 2025
|