A method of manufacturing an aircraft aerofoil, e.g. winglet, wing, spoiler, flap. The airfoil comprises first and second covers 140, 130, leading and trailing edges. The covers are joined at a trailing edge interface 150. The first cover is formed by a plurality of laid-up fibre plies, obtaining a preform. The preform is laid up with a ramp (143, figure 3) decreasing in thickness towards the preform trailing edge. The preform is cured with the ramp forming a contact surface of the first cover. The trailing edge interface is assembled by engaging contact surfaces of the covers. Fiber plies may terminate in a staggered fashion at the ramp. An apex (147) may be formed between ramps of increasing (145) and decreasing (143) thickness. The ramp may comprise a cover ply covering a stack of fibre plies. The preform may be cured in contact with a mould. Dry-fibre plies may be impregnated with a matrix. Upper and/or lower panels may have a thickened interface region (figure 6).


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    Title :

    Method of manufacturing aircraft aerofoil


    Contributors:

    Publication date :

    2022-04-27


    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 / B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse / 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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