Stiffening structure for an aircraft door or panel

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...

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Bibliographische Detailangaben
Hauptverfasser:	Paul Henry Robinson, Christopher Philip Dance, Matthew George Collinson, Elaine Lois Arnold, Philip Michael Johnson, Richard John Scaife, Craig Philip Atkins, Gawain Horrocks, Jamie Adam Smith
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS MAKING GRANULES OR PREFORMS PERFORMING OPERATIONS PREPARATION OR PRETREATMENT OF THE MATERIAL TO BESHAPED PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIALCONTAINING PLASTICS SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	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.