Structural element of an aircraft fuselage

Details Structural element of an aircraft fuselage Structural element of an aircraft fuselage

B - Operations, Transporting

64

C

B64C 1/06 (2006.01) B64C 1/40 (2006.01)

Patent

CA 2682969

The structural element of an aircraft fuselage, with stringers (20, 30; 40; 50; 60) running in the longitudinal direction of the aircraft fuselage and ribs (80) running transversely to the stringers (20, 30; 40; 50; 60) in the circumferential direction of the fuselage. According to the invention, at least one of the stringers (30; 40; 50; 60) running in the longitudinal direction of the aircraft fuselage is designed as a fastening rail for elements (100, 110) to be installed in the aircraft fuselage.

L'invention porte sur un élément structurel de fuselage d'avion, comportant des lisses (20, 30; 40; 50; 60) dirigées dans le sens longitudinal du fuselage et des nervures (80) perpendiculaires aux lisses (20, 30; 40; 50; 60) et dirigées dans le sens de la circonférence du fuselage. Selon l'invention, l'une au moins des lisses (30; 40; 50; 60) sert de rail de fixation d'éléments (100, 110) à installer dans le fuselage.

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