A fairing mechanism for an aircraft flap includes: a slide rail portion formed with a rail extending obliquely in a fore-aft direction of an aircraft, wherein a slider is disposed on the rail, and the slider is capable of sliding along the rail; a fairing, the front portion of which is provided with at least one front connector, wherein the front connector is connected to the sliding rail portion in a hinged mode, and the fairing further comprises at least one middle connector; and at least one pull rod, wherein one end of the pull rod is connected to the sliding piece in a hinged mode, and the other end of the pull rod is connected to the middle connector in a hinged mode. The fairing mechanism is simplified in structure, the operation reliability of the driving mechanism is improved, and meanwhile, the machining and mounting difficulty is lowered.
一种用于飞机襟翼的整流罩机构包括:滑轨部,该滑轨部形成有轨道,轨道沿着飞机的前后方向且倾斜地延伸,在轨道上设置有滑动件,滑动件能够沿着轨道滑动;整流罩,该整流罩的前部具有至少一个前接头,其中,前接头可铰转地连接于滑轨部,且整流罩还包括至少一个中接头;以及至少一个拉杆,拉杆的一端可铰转地连接于滑动件,另一端可铰转地连接于中接头。该整流罩机构结构简化,在提高驱动机构运行可靠性的同时降低了加工和安装的难度。
Flap fairing mechanism
一种襟翼整流罩机构
05.11.2021
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
Europäisches Patentamt | 2018
|Europäisches Patentamt | 2017
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