Patent ID: 8376276

Claim:
A load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface, wherein the load introduction structure is connected by a non-load-increasing connection to the fuselage airframe structure of the aircraft that creates an uncoupling effect in order to compensate for at least one of load-induced deformations or thermally-induced deformations of the fuselage airframe structure; wherein the fuselage airframe structure is formed by a plurality of ring frames which are covered externally by a fuselage airframe skin, the lateral frames each being connected to the ring frames, and wherein the lateral frames are connected to the ring frames by a plurality of rods comprising an articulated rod connection, wherein each lateral frame comprises at least two lateral frame segments, wherein each lateral frame segment comprises at least one base frame segment, wherein each base frame segment comprises upper longitudinal struts which are connected at the ends thereof to vertical struts, and wherein flanges are arranged on the vertical struts in each of which a slot is formed, wherein the slots enable the base frame segments to move relative to one another in a longitudinal direction with the formation of a gap to compensate a change in length of the fuselage airframe structure.