A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.
Wing assembly having discretely stiffened composite wing panels
2023-05-09
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
WING ASSEMBLY HAVING DISCRETELY STIFFENED COMPOSITE WING PANELS
European Patent Office | 2022
|Design charts for longitudinally stiffened wing compression panels
Engineering Index Backfile | 1949
|DESIGN CHARTS for Longitudinally Stiffened Wing Compression Panels
SAE Technical Papers | 1949
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