Patent ID: 8628041

Claim:
An aircraft structure comprising: a skin ( 28 ) reinforced in two directions, a first family of stiffeners called stringers ( 30 ) arranged in a longitudinal direction of an aircraft and reinforcing the skin in the longitudinal direction, the stringers connected to an inside surface of the skin; and a second family of stiffeners called frames ( 32 ) arranged in planes perpendicular to the longitudinal direction and reinforcing the skin in the perpendicular to the longitudinal direction, the frames taking up of orbital forces, wherein, at least one frame ( 32 ) has a hollow cross-section is delimited by a plurality of connected flat sections ( 34 , 36 , 38 , 40 ) together defining a closed profile, the at least one frame ( 32 ) is a single piece not derived from an assembly of plural parts, a first of the flat sections ( 34 ) is in contact with the skin, and a second of the flat sections ( 36 ) is connected to said first flat section ( 34 ), a third of the flat sections ( 38 ) is connected to said second flat section ( 36 ), a fourth of the flat sections ( 40 ) is connected to said third flat section ( 38 ), and said fourth flat section ( 40 ) is connected to said first flat section ( 34 ) thereby defining a closed, right trapezoidal profile.