A component for transferring a load applied to an opening 21 in the component to another location of the component comprises a matrix material and at least one longitudinal reinforcing clement 23 embedded in the matrix material which is under tension, arranged in a loop around the opening 21 and comprises a section that is aligned with the load path between the opening 21 and the other location of the component. The reinforcing element 23 contacts one or more pins 72a & 72b embedded within the matrix material and located inside the loop. The component comprises a further reinforcing element 24 arranged in a loop around the opening 21 and which forms at least a part of the surface of the opening 21. The component can be an aircraft rib which supports landing gear or an engine and can be made from an aluminium or titanium matrix with an aluminium oxide fibre, carbon fibre or silicon carbide fibre reinforcing element. The component can be made by casting, additive manufacturing, beam deposition or hot isostatic pressing.


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    Titel :

    Load-transferring components


    Beteiligte:
    WILLIAM TULLOCH (Autor:in) / FRASER WILSON (Autor:in)

    Erscheinungsdatum :

    16.09.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B22D CASTING OF METALS , Gießen von Metallen / B22F Verarbeiten von Metallpulver , WORKING METALLIC POWDER / B23K Löten , SOLDERING OR UNSOLDERING / B33Y ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING , Additive (generative) Fertigung, d. h. die Herstellung von dreidimensionalen [3D] Bauteilen durch additive Abscheidung, additive Agglomeration oder additive Schichtung, z. B. durch 3D- Drucken, Stereolithografie oder selektives Lasersintern / B64C AEROPLANES , Flugzeuge



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