The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.
ELÉMENT DE STRUCTURE DE FUSELAGE D'AÉRONEF ANTI DÉVERSEMENT
STRUCTURAL ELEMENT FOR AN AIRCRAFT FUSELAGE THAT PREVENTS LATERAL-TORSIONAL BUCKLING
STRUKTURELEMENT FÜR EINEN FLUGZEUGRUMPF ZUR VERHINDERUNG VON LATERAL-TORSIONALEM KNICKEN
2016-03-09
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
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