The embodiment of the invention provides a double-hinge rudder structure of a large and medium-sized aircraft. The double-hinge rudder structure comprises a front rudder (1) and a rear rudder (2), wherein the front rudder (1) is connected to a suspension support arm at the rear edge of a vertical stabilizer of an airplane; and the rear rudder (2) is connected to the front rudder (1). The double-hinge rudder structure is composed of a front rudder structure and a rear rudder structure, and the deflection angle of a rear rudder is twice that of a front rudder. According to the double-hinge rudder structure, the rudder surface area and the deflection angle of the rudder are increased, and the course correction and steering speed of an airplane are increased.
本发明实施例提供一种大中型飞机的双铰链方向舵结构,包括:前方向舵(1)和后方向舵(2);前方向舵(1)连接在飞机的垂直安定面后缘悬挂支臂上;后方向舵(2)连接在前方向舵(1)上。该双铰链方向舵结构由前方向舵结构与后方向舵结构两部分组成,后方向舵的偏转角度为前方向舵的2倍。该双铰链方向舵结构增大了方向舵的舵面面积和偏转角度,提高了飞机的航向修正和转向速度。
Double-hinge rudder structure of large and medium-sized airplanes
大中型飞机的双铰链方向舵结构
2020-04-14
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
Rudder Control Problems on Four-Engined Airplanes
SAE Technical Papers | 1940
|Hinge type rudder system underwater inspection structure
Europäisches Patentamt | 2024
|