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
COMPOSANTE DE FUSELAGE RENFORCEE AINSI QUE METHODES ET APPAREIL DE FABRICATION D'UNE COMPOSANTE DE FUSELAGE RENFORCEE
2016-12-24
Patent
Electronic Resource
English
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