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US 8,757,545 B2Granted
Segment of a fuselage of an aircraft
AssigneeAirbus Operations GmbH
InventorsJan Lesemann, Michael Meyer, Bernd Trahmer, Ralph Sturm
Life of this patent
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Abstract
According to an exemplary embodiment of the invention a fuselage segment of an aircraft fuselage is provided, which aircraft fuselage comprises four different radii of curvature, wherein two radii of curvature comprise center points that are not situated on a vertical symmetry axis of the fuselage segment.
Claims13
A fuselage segment for an aircraft fuselage,
- wherein the fuselage segment comprises a curved external surface with a first radius of curvature (R1), a second radius of curvature (R2), a third radius of curvature (R3) and a fourth radius of curvature (R4),
- 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 (R1) describes a first circumferential section (UA1) of the fuselage segment at an angle α,
- wherein the second radius of curvature (R2) describes a second circumferential section (UA2) of the fuselage segment at an angle β, the second circumferential section (UA2) being adjacent to the first circumferential section (UA1);
- wherein the third radius of curvature (R3) describes a third circumferential section (UA3) of the fuselage segment at an angle γ, the third circumferential section (UA3) being adjacent to the second circumferential section (UA2);
- wherein the fourth radius of curvature (R4) describes a fourth circumferential section (UA4) of the fuselage segment at an angle δ, the fourth circumferential section (UA4) being adjacent to the third circumferential section (UA3);
- and
- wherein the following applies:
- α<β, β>γ and γ<δ.
7 more elements
An aircraft fuselage comprising a fuselage segment comprising:
- a curved external surface with a first radius of curvature (R1), a second radius of curvature (R2), a third radius of curvature (R3) and a fourth radius of curvature (R4),
- 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 (R1) describes a first circumferential section (UA1) of the fuselage segment at an angle α, the second circumferential section (UA2) being adjacent to the first circumferential section (UA1);
- wherein the second radius of curvature (R2) describes a second circumferential section (UA2) of the fuselage segment at an angle β, the third circumferential section (UA3) being adjacent to the second circumferential section (UA2);
- wherein the third radius of curvature (R3) describes a third circumferential section (UA3) of the fuselage segment at an angle γ, the fourth circumferential section (UA4) being adjacent to the third circumferential section (UA3);
- wherein the fourth radius of curvature (R4) describes a fourth circumferential section (UA4) of the fuselage segment at an angle δ, and
- wherein the following applies:
- α<β, β>γ and γ<δ.
6 more elements
An aircraft comprising an aircraft fuselage comprising a fuselage segment comprising:
- a curved external surface with a first radius of curvature (R1), a second radius of curvature (R2), a third radius of curvature (R3) and a fourth radius of curvature (R4),
- 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 (R1) describes a first circumferential section (UA1) of the fuselage segment at an angle α, the second circumferential section (UA2) being adjacent to the first circumferential section (UA1);
- wherein the second radius of curvature (R2) describes a second circumferential section (UA2) of the fuselage segment at an angle β, the third circumferential section (UA3) being adjacent to the second circumferential section (UA2);
- wherein the third radius of curvature (R3) describes a third circumferential section (UA3) of the fuselage segment at an angle γ, the fourth circumferential section (UA4) being adjacent to the third circumferential section (UA3);
- wherein the fourth radius of curvature (R4) describes a fourth circumferential section (UA4) of the fuselage segment at an angle δ, and
- wherein the following applies:
- α<β, β>γ and γ<δ.
6 more elements
Dependencies are inferred from the claim text.