| 摘要 |
The invention pertains to a fuselage segment (2) that extends in a longitudinal fuselage segment axis (A) and is closed in a circumferential direction (U) around this longitudinal fuselage segment axis, wherein the fuselage segment features: a plurality of shell components (4) for forming a skin of the fuselage segment (2) that respectively feature two first shell component edges (6) extending along a longitudinal shell component direction (LS) and two second shell component edges (10) extending along a lateral shell component direction (LB), wherein the shell components (4) are respectively connected to at least one adjacent shell component (4) along at least one first shell component edge (6) and along at least one second shell component edge (10), and wherein at least the direction of a tangent (T) on first shell component edges (6), on which two respective shell components (4) are connected to one another, and/or on second shell component edges (10), on which two respective shell components (4) are connected to one another, as well as to a method for manufacturing such a fuselage segment (2).
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