TRONCON DE FUSELAGE D'AERONEF EN MATERIAU COMPOSITE A PROFIL INTERIEUR CONSTANT

The section has an internal structure including frames (15) forming a radial structure of a fuselage, and stiffeners (14) forming a longitudinal structure of the fuselage, where the stringers have constant height. A composite skin (13) encloses the internal structure. The composite skin has thicknes...

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Bibliographische Detailangaben
Hauptverfasser:	GAUDIN JOCELYN, MEYER CEDRIC
Format:	Patent
Sprache:	fre
Schlagworte:	AEROPLANES AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS 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:	The section has an internal structure including frames (15) forming a radial structure of a fuselage, and stiffeners (14) forming a longitudinal structure of the fuselage, where the stringers have constant height. A composite skin (13) encloses the internal structure. The composite skin has thickness that is variable along a central longitudinal axis of an aircraft by superposition and interweaving of laps of sheets, so as to assure a regular and constant inner profile along the axis. An independent claim is also included for a method for fabricating a skin of a composite fuselage section of an aircraft.