A stiffening structure for an aircraft panel or door and method for fabricating the same, the method comprising: providing a thermoplastic continuous fibre-reinforced composite material comprising a plurality of continuous fibres embedded in a thermoplastic polymer matrix; cutting the thermoplastic continuous fibre-reinforced composite material into a plurality of short fibre-reinforced composite pellets; heating the plurality of short fibre reinforced composite pellets so as to cause the plurality of short fibre-reinforced composite pellets to fuse together; cooling the fused together pellets to form a consolidated sheet of thermoplastic short fibre-reinforced composite material; and moulding the consolidated sheet to form the stiffening structure having a top wall, a bottom flange, and side walls disposed between the top wall and the bottom flange. Preferably, the fibres may be carbon fibres and the thermoplastic matric is a polyaryletherketone. The stiffening structure may comprise a plurality of connected stiffening elements oriented in multiple directions.


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    Titel :

    Stiffening structure for an aircraft door or panel



    Erscheinungsdatum :

    17.06.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B64C AEROPLANES , Flugzeuge / B29B PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED , Vorbereiten oder Vorbehandeln der zu verformenden Masse / B29D PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE , Herstellen besonderer Gegenstände aus Kunststoff oder aus Stoffen in plastischem Zustand



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