A method of repairing a composite beam 130, the method comprising: removing material from a damaged area 140 of the composite beam to form a cut out region 141; machining a plurality of elongate slots 142 into the composite beam, the elongate slots each spanning across the damaged area, the elongate slots extending into the composite beam to a depth greater than a depth of the cut out region; introducing a plurality of reinforcing inserts 152 into the respective elongate slots and fixing the reinforcing inserts into the slots with adhesive. The composite beam may include a fibre reinforced composite element through which the elongate slots extend, and a foam core. The reinforcing inserts may each be formed of a fibre reinforced composite material, the method may include inserting one or more filler pieces 151 into the cut out region to complete the profile of the composite beam, and laying one or more overlapping plies, 154 so as to extend over and cover the one or more filler pieces and the reinforcing inserts. A repaired composite beam, structural assembly and aircraft wing comprising the repaired beam are also provided.


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    Titel :

    Method of repairing a composite beam


    Beteiligte:

    Erscheinungsdatum :

    18.10.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / 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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