Patent ID: 8651421

Claim:
An aircraft fuselage structure which is constructed from a plurality of shells which are joined together, each shell forming part of the aircraft fuselage and comprising: a support structure, and a skin which is arranged on the support structure and outwardly seals the aircraft fuselage in a compression-proof manner, wherein the plurality of shells of the aircraft fuselage structure comprises: an upper and side shell, and a lower shell, of which the lower shell has a radius which is, averaged over the circumference, more than 1.2 times the radius, averaged over the circumference, of the upper and side shell, the upper and side shell and the lower shell being joined together at transition regions extending in the longitudinal direction of the aircraft, wherein the support structure of the lower shell is designed in terms of the strength of the support structure in such a manner that the support structure is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember, wherein, the aircraft fuselage structure is produced in a hybrid construction with the lower shell being produced from light metal components and the upper and side shell being produced from fiber-reinforced components; wherein the upper and side shell and the lower shell are connected in the transition regions by a glass-fiber and aluminum composite tab with glass-fiber layers and light metal layers arranged in an alternating manner in a laminate, and wherein the lower shell has a central region which extends from the center of the aircraft to both sides and has a constant radius and has a smaller radius at the sides in the vicinity of the transition regions, so that the lower shell merges smoothly into the upper and side shell.