Patent ID: 8757545

Claim:
A fuselage segment for an aircraft fuselage, wherein the fuselage segment comprises a curved external surface with a first radius of curvature (R 1 ), a second radius of curvature (R 2 ), a third radius of curvature (R 3 ) and a fourth radius of curvature (R 4 ), wherein the four radii of curvature are situated in the same plane, and wherein the four radii of curvature comprise different centre points; wherein the first radius of curvature (R 1 ) describes a first circumferential section (UA 1 ) of the fuselage segment at an angle α, wherein the second radius of curvature (R 2 ) describes a second circumferential section (UA 2 ) of the fuselage segment at an angle β, the second circumferential section (UA 2 ) being adjacent to the first circumferential section (UA 1 ); wherein the third radius of curvature (R 3 ) describes a third circumferential section (UA 3 ) of the fuselage segment at an angle γ, the third circumferential section (UA 3 ) being adjacent to the second circumferential section (UA 2 ); wherein the fourth radius of curvature (R 4 ) describes a fourth circumferential section (UA 4 ) of the fuselage segment at an angle δ, the fourth circumferential section (UA 4 ) being adjacent to the third circumferential section (UA 3 ); and wherein the following applies: α<β, β>γ and γ<δ.