The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.


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    Title :

    Method of manufacturing a composite sandwich panel for an aircraft propulsion unit


    Contributors:

    Publication date :

    2019-03-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    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 / B28B Formgeben von Ton oder anderen keramischen Stoffzusammensetzungen, Schlacke oder von Mischungen, die zementartiges Material enthalten, z.B. Putzmörtel , SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS, SLAG OR MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / C04B Kalk , LIME / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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