The invention provides a blade front edge cap repairing method, belongs to the field of composite material blade repairing and relates to a front edge cap and blade bonding process method. The blade front edge cap repairing method is safe and reliable in quality and simple and feasible in operation and namely is a front edge cap changing process. Through bonding peel strength test, control tower operation test and flight test, the blade front edge cap repairing method is proved to be safe and reliable in quality in the field of edge cap repair. Meanwhile, the blade front edge cap repairing method is simple and convenient to operate, reduces the cost for repair and maintenance and shortens the maintenance cycle of blade front edge caps.


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    Title :

    Blade front edge cap repairing method


    Contributors:

    Publication date :

    2015-06-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    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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