Patent ID: 8534605

Claim:
An aircraft fuselage structure comprising: frames running in a circumferential direction of the fuselage; stringers running in a longitudinal direction of the fuselage; and a skin which is arranged on the frames and the stringers and outwardly seals the aircraft fuselage in a compression-proof manner; wherein the aircraft fuselage structure comprises: a plurality of prefabricated integral units which each run in the circumferential direction of a fuselage segment, and a plurality of skin elements comprising stringers and a skin, and wherein each of the integral units further comprises at least: a frame; and a plurality of force-transmission combs for connection to the skin elements, wherein the plurality of skin elements are fixed to the plurality of prefabricated integral units in a frictional and/or interlocking manner via the plurality of force-transmission combs, wherein the force-transmission combs formed on the integral units are directly connected to the skin elements, and wherein a plurality of glass-fiber and aluminum composite tabs are provided at a plurality of connecting points of the skin elements and the plurality of force-transmission combs, and wherein the plurality of glass-fiber and aluminum composite tabs are capable of compensating for different thermal coefficients of expansion of light metal alloys and fiber-reinforced plastics.