Aircraft structure including stiffener edge junctions

Details Aircraft structure including stiffener edge junctions Aircraft structure including stiffener edge junctions

B - Operations, Transporting

64

C

B64C 1/06 (2006.01) B64C 1/12 (2006.01)

Patent

CA 2702908

The invention relates to an aircraft structure (1) including stiffened panels (5) assembled at junctions, whereat the stiffeners (9) are interrupted. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. Said 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 invention includes a doubler (26) necessitating at most one additional part per panel junction zone for all of the interrupted stiffeners in said zone.

La présente invention se rapporte à une structure d'avion (1) comportant des panneaux (5) raidis assemblés sans conti-nuité de raidisseurs (9) à la jonction. Un avion comporte plusieurs panneaux pour former son fuselage, ses empennages et sa voilure. Ces panneaux comportent des raidisseurs qui sont interrompus à chaque jonction de panneaux. Cependant, les efforts subits par les raidisseurs doivent être transmis malgré les interruptions. Les solutions connues nécessitent au moins une pièce supplémentaire par raidisseur et par interruption. L'invention prévoit pour résoudre ce problème d'intégrer un doubleur (26) permettant d'avoir au plus une pièce supplémentaire par zone de jonction de panneaux pour tous les raidisseurs interrompus dans cette zone.

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