Patent ID: 8123166

Claim:
A primary structure of an aircraft fuselage comprising: at least one reinforcing frame that extends along a cross section of the aircraft essentially perpendicular to its long dimension, at least one crossbeam fastened to the reinforcing frame, at least a first strut linked at one end to the crossbeam and at the other end to the reinforcing frame, at least a second strut that has one end fastened to the structure below the end of the first strut fastened to the reinforcing frame, and another end linked to the first strut through an intermediate sliding linkage, and a deformable member able to absorb energy by irreversible elongation, with this deformable member having one end fastened to the end of the first strut fastened to the reinforcing frame, and another end fastened to the end of the second strut linked to the first strut by the sliding linkage, so that in case of a crash, the compressive forces press against the second strut, so that the end of this second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.