The present invention describes a fuselage structure (1) for an aircraft, having a frame structure (2), which extends in a circumferential direction (U) and has a first connecting section (21) and a second connecting section (22), which is arranged spaced apart from the first connecting section (21), a reinforcing structure (3), which extends between the first and the second connecting sections (21; 22) and is connected respectively to the first and the second connecting sections (21; 22), an outer shell (4), which is secured on an outer side (3A) of the reinforcing structure (3), and an inner shell (5), which is secured on an inner side (3B) of the reinforcing structure (3). The reinforcing structure (3) has a profiled cross section when viewed in a longitudinal direction (L) extending transversely to the circumferential direction (U) and, together with the inner shell (5) and the outer shell (4), forms a plurality of channels (6), which are adjacent to one another in the circumferential direction (U) and each extend in the longitudinal direction (L). An aircraft (100) which has a fuselage structure (1) of this kind is furthermore described.
FUSELAGE STRUCTURE FOR AN AIRCRAFT
STRUCTURE DE FUSELAGE DESTINEE A UN AERONEF
2019-11-17
Patent
Elektronische Ressource
Englisch