| 摘要 |
An aircraft fuselage structure is described, which is constructed from a plurality of shells (11, 12) which are joined together, each form part of the aircraft fuselage (10) and comprise a support structure (13, 13a, 14, 14a) and a skin (15, 16) which is arranged on the latter and outwardly seals the aircraft fuselage (10) in a compression-proof manner. According to the invention, the aircraft fuselage structure comprises an upper and side shell (11) and a lower shell (12), of which the lower shell (12) has a radius (R2) which is essentially significantly larger than the radius (Rl) of the upper and side shell (11), the upper and side shell (11) and the lower shell (12) being joined together at transition regions (18, 19) extending in the longitudinal direction of the aircraft, and the support structure (13, 13a) of the lower shell (12) being designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell (12) without the use of a main crossmember. |
