Method comprising cutting fibre band pieces from a spreader fiber band and fixing the fibres in predetermined positions on a core through use of a binder. Preferably a second set of relatively longer fibre band pieces are also placed on the exterior of the core. More preferably the shorter fibres and longer fibres are placed on opposite sides of the core. The length or width of the shorter fibres may be smaller than the width of the longer fibres. A composite frame may also be provided, the core being provided to the frame and the fibre positions being relative to the frame. Multiple layers of the short fibers may be included. Cutting and placing of the fibres may be automated using an arm assembly. The parts made are preferable avionic parts. A second method for forming a panel assembly is included comprising disposing a first layer of longer fibres in a determined position, disposing a core and second layer of fibres at a second set of positions and affixing the first and second layers through use of a binder. The core may be foam, the fibres may be carbon.


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    Title :

    Method for forming stiffened composite parts


    Contributors:

    Publication date :

    2018-05-23


    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 / B64C AEROPLANES , Flugzeuge



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