A stiffened fuselage component (10) made of a fiber reinforced composite material, in particular for use in an aircraft, comprises a skin element (12) and a plurality of elongated stiffening elements (18) forming a stiffening element pattern comprising a plurality of node points (20) and being attached to an inner surface (16) of the skin element (12), wherein at least some of the node points (20) are defined by an intersection of at least two stiffening elements (18) at an acute angle or an obtuse angle, and wherein at least some of the elongated stiffening elements (18) are shaped so as to define an internal cavity (22) delimited by an inner surface (24) of the stiffening elements (18) and covered by the skin element (12).
STIFFENED FUSELAGE COMPONENT AS WELL AS METHOD AND APPARATUS FOR MANUFACTURING A STIFFENED FUSELAGE COMPONENT
VERSTEIFTE RUMPFKOMPONENTE SOWIE VERFAHREN UND VORRICHTUNG ZUR HERSTELLUNG EINER VERSTEIFTEN RUMPFKOMPONENTE
COMPOSANT DE FUSELAGE RIGIDIFIE ET PROCEDE ET APPAREIL DE FABRICATION D'UN COMPOSANT DE FUSELAGE RIGIDIFIE
2019-08-07
Patent
Electronic Resource
English
European Patent Office | 2016
|European Patent Office | 2016
|Stiffened Composite Fuselage Barrel Optimization
British Library Conference Proceedings | 2012
|Damage Tolerance of Fuselage Welded Stiffened Panels
British Library Conference Proceedings | 2004
|Integrally stiffened carbon fibre aircraft fuselage structure
TIBKAT | 1982
|