Patent ID: 8746621

Claim:
An aircraft structure, comprising: a fuselage a rib extending the fuselage and belonging to a wing box; an upper panel of the wing box connected to the fuselage and the rib; and stiffening frames of the fuselage extending in a transverse section of the aircraft between a lower end and an upper end of the stiffening frame, each stiffening frame including: a core extending between the lower end and the upper end of the stiffening frame, heels at a free end of the stiffening frame, wherein the heels are perpendicular to the core, and a base plate at an end opposite to the free end of the stiffening frame, wherein at least the cores of the stiffening frames contact notches in the wing box panel, and extend continuously through the notches, wherein the lower end of the stiffening frames stiffen the rib, and wherein the wing box panel comprises first notches oriented toward the transverse sections of the aircraft to allow the cores of the frames to pass, and second notches oriented in an axial direction of the aircraft to free the passage for base plates of the frames bearing on the fuselage and the rib.