Patent ID: 8919696

Claim:
A method for stiffening a skin field of an aircraft fuselage, the method comprising: providing a skin field for an aircraft fuselage; manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners, wherein the integral lattice-shaped stiffening structure includes mounts extending in a transverse direction and connecting the longitudinal stiffeners with each other, the mounts having a profile including a foot configured to be attached to the skin field and a flange extending orthogonally from the foot and outwardly from the stiffening structure such that the mounts are configured to align and connect, by the flanges, circumferential stiffeners to the stiffening structure, the manufacturing including providing a tool having longitudinal elements and sunken areas adapted to form the mounts, the sunken areas extending between the longitudinal elements; and connecting the stiffening structure to the skin field.