| 摘要 |
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. |
