Aircraft fuselage structure having a grid-stiffened panel

A structure for a fuselage of an aircraft, said structure comprising:

• a skin having an outer face and an inner face machined as a grid-stiffened panel,
• a plurality of frames, each frame taking a shape of a cross section of the fuselage and the frames being arranged one after another along a longitudinal direction of the fuselage, an outer perimeter of each frame being secured to the inner face of the skin,
• a plurality of stringers extending parallel to the longitudinal direction of the fuselage, each stringer extending across multiple frames, passing through the frames at an opening provided to that end in each frame, and each stringer being pressed against the inner face of the skin and secured thereto, and
• in an upper part and in a lower part of the fuselage, a torsion box which extends parallel to the longitudinal direction of the fuselage, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face of the skin.