Composite components (50) are joined by firstly locating portions of two separate composite components in adjacent or overlapping relation, to provide a join area. The components (50) are substantially fully cured, with the portions located within the join area being uncured or partially cured. At least one pressure chamber (3, 4) is located over the join area, the pressure chamber including a displacement abutment face (5, 6). Fluid is circulated at an elevated temperature and pressure through the pressure chamber to compress the join area with the displaceable abutment face of the pressure chamber and elevate its temperature in a controlled manner over time to effect curing of the join area.


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    Titel :

    Method of joining composite components


    Weitere Titelangaben:

    Verfahren zum Verbinden von Verbundbauteilen
    Méthode de collage d'éléments composites


    Beteiligte:
    GRAHAM NEIL (Autor:in)

    Erscheinungsdatum :

    2015-12-02


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / 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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