Patent ID: 8534605
Filing Date: 2013-09-17
Classification: B64C,Y10T

Abstract:
1. 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: 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.