Fuselage segment and method for manufacturing a fuselage segment

摘要

Provided is a fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around this longitudinal fuselage segment axis. The fuselage segment features a plurality of shell components for forming a skin of the fuselage segment that respectively feature two first shell component edges extending along a longitudinal shell component direction and two second shell component edges extending along a lateral shell component direction. The shell components are respectively connected to at least one adjacent shell component along at least one first shell component edge and along at least one second shell component edge. Methods for manufacturing such a fuselage segment are also provided.

主权项

1. A fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around the longitudinal fuselage segment axis, wherein the circumferential direction lies in a reference radial plane, relative to which the longitudinal fuselage segment axis extends perpendicularly, and wherein the fuselage segment comprises:
at least two pluralities of shell components each of which shell components respectively feature two first shell component edges lying opposed to each other and extending along a lateral shell component direction and two second shell component edges lying opposed to each other and extending along a longitudinal shell component direction, wherein the shell components of each plurality of shell components are respectively connected to each other at their first shell component edges such that the respective plurality of shell components forms a ring-shaped skin section of the fuselage segment and has a centerline, which is defined as a connection line of the centers of the shortest distances between the second shell component edges respectively lying opposed to each other, and which forms a closed line which lies in a first radial plane which is inclined with regard to the reference radial plane by at least 5 degrees, wherein at least two ring-shaped skin sections are connected to each other at the second shell component edges of the shell components of the adjacent ring-shaped skin sections.