Provided are stiffened stringer panels with integrated shim structures. An example composite panel comprises a skin member having an inner surface, and a stringer positioned on the inner surface. The stringer comprises a first flange portion and a second flange portion with the first flange portion and the second flange portion contacting the inner surface. The composite panel further comprises an integrated shim positioned on the first flange portion. The integrated shim may comprise a sacrificial material configured to be trimmed to the desired geometry. The sacrificial material may comprise a glass fiber reinforced plastic fabric pre-impregnated with resin. The integrated shim may be configured to interface with internal support structures of a wing assembly. The integrated shim may be configured to he machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.


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    Title :

    STIFFENED COMPOSITE PANEL WITH INTEGRATED SHIM


    Contributors:

    Publication date :

    2022-06-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / 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



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