A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in. Consequently there is no need to provide complex stiffening structures within the fairing element.
Load-bearing fairing element for a flap adjustment mechanism and aircraft having such a fairing element
2018-03-27
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2017
|European Patent Office | 2015
|European Patent Office | 2018
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