The invention relates to a central wing box for an aircraft, comprising a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. According to the invention, a secondary rib comprises two stiffeners (410A, 410B), a first stiffener (410A) extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener (410B) extending adjacent to the bottom panel and to the other of the front spar and the rear spar. The invention employs a reduced number of components, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.
INTEGRATED RIBS FOR CENTRAL WING BOX
NERVURES INTEGREES DESTINEES A UN CAISSON D'AILE
2017-03-04
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Engineering Index Backfile | 1930
The design of airplane wing ribs
Engineering Index Backfile | 1931
|The design of airplane wing ribs
TIBKAT | 1930
|