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.


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    Title :

    Wing assembly having discretely stiffened composite wing panels


    Contributors:

    Publication date :

    2023-05-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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

    BEHZADPOUR FOROUZAN / LEVINE DANIEL M | European Patent Office | 2022

    Free access

    Dynamic response and noise transmission of discretely stiffened composite panels

    LYRINTZIS, CONSTANTINOS / VAICATIS, RIMAS | AIAA | 1988


    Random response and noise transmission of discretely stiffened composite panels

    LYRINTZIS, CONSTANTINOS S. / VAICAITIS, RIMAS | AIAA | 1990


    Design charts for longitudinally stiffened wing compression panels

    Dow, N.F. | Engineering Index Backfile | 1949