In one embodiment, a system includes a first end effector configured to press a selected area of an aircraft wing skin panel against a corresponding area of an underlying wing support structure with a downward force, drill a hole within the selected area, the hole extending through the skin panel and the support structure, and insert an elongated shaft of a fastener into the hole. The system includes a mechanism configured to locate the first end effector relative to the selected area. The system can further include a second end effector configured to press the corresponding area of the support structure against the selected area of the skin panel with an upward force that is opposite in direction to the downward force, and a mechanism configured to locate the second end effector relative to the corresponding area of the support structure.


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    Title :

    Systems and methods for assembling aircraft wing skins


    Contributors:

    Publication date :

    2018-01-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16B DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES , Vorrichtungen zum Befestigen oder Sichern von Konstruktionselementen oder Maschinenteilen, z.B. Nägel, Bolzen, Schrauben, Sprengringe, Klemmen, Klammern oder Keile / B64C AEROPLANES , Flugzeuge / 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



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