Airbus Operations (s.a.s.)

Helene Cazeneuve

Bruno Cacciaguerra

Jean-Claude Lacombe

David Andissac

An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.

Splicing of omega-shaped stiffeners at a circumferential joint in an aircraft fuselage

An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.

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Plaisance du Touch, France

Helene Cazeneuve