The invention discloses a leading-edge detachable type experiment wing structure based on a piezoelectric deicing system. The structure comprises two leading-edge parts, one front-segment crossbeam, two rear-segment parts and one rear-segment crossbeam, wherein each leading-edge part and the rear-segment crossbeam are respectively arranged at the two ends of each rear-segment part, the rear-segment parts and the leading-edge parts are connected through the front-segment crossbeam, the two leading-edge parts are parallel to each other, the two leading-edge parts are symmetrical along a longitudinal center line of the experiment wing structure, and the spacing between the two leading-edge parts can be randomly adjusted. According to the invention, the leading-edge parts can be detachable and adjusted, and wing models with different wing expansion direction dimensions can be combined, such that diversity of research on piezoelectric deicing methods can be realized according to different adjustment wing structures of research objects.


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    Title :

    Leading-edge detachable type experiment wing structure based on piezoelectric deicing system


    Contributors:
    MIAO BO (author) / ZHU CHUNLING (author) / ZHU CHENGXIANG (author) / WANG YUAN (author)

    Publication date :

    2016-01-20


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / 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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