Fuselage component for an aircraft, method for producing a fuselage component, and aircraft

Patent metadata

Field	Value
Publication number	US-11560211-B2
Application number	US-201916720147-A
Country	US
Kind code	B2
Filing date	Dec 19, 2019
Priority date	Dec 20, 2018
Publication date	Jan 24, 2023
Grant date	Jan 24, 2023

Abstract

A fuselage component for an aircraft, including a shell part composed of a fiber composite material and a stiffening structure which is connected to an inner surface of the shell part and has shaped parts composed of a fiber composite material, wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section. The shaped parts are arranged in the form of parquetry with overlapping profile edges. As a result, the overlapping profile edges form stiffening profiles intersecting at an intersection. Furthermore, an aircraft which has at least one such fuselage component and a method for producing a fuselage component are described.

First claim

The invention claimed is:

1. A fuselage component for an aircraft, comprising:
a shell part of flat extent and composed of a fiber composite material; and
a stiffening structure which is connected to an inner surface of the shell part and has a multiplicity of shaped parts composed of a fiber composite material;
wherein the shaped parts each have a flat base section which extends along the inner surface of the shell part, and a step-shaped profile edge which extends in an encircling manner around the base section, wherein each of the shaped parts comprises an interruption in a region of an interruption corner;
wherein the shaped parts are arranged with overlapping profile edges such that the overlapping profile edges form stiffening profiles intersecting at an intersection in a region of an intersection corner.

2. The fuselage component according to claim 1 , wherein a load-bearing tape composed of a fiber composite material is connected to each stiffening profile and extends beyond the intersection.

3. The fuselage component according to claim 1 , wherein the base sections of the shaped parts are of rectangular design, wherein the profile edge of a respective shaped part in each case has two mutually opposite first profile sections which extend in a first direction, and two mutually opposite second profile sections which extend between the first profile sections in a second direction, wherein the first profile sections of in each case two shaped parts that are adjacent in the second direction overlap such that they form a first stiffening profile extending in the first direction, wherein the second profile sections of in each case two shaped parts that are adjacent in the first direction overlap such that they form a second stiffening profile which extends in a second direction and intersects the first stiffening profile at an intersection, and wherein a load-bearing tape is connected to each of the overlapping first profile sections and extends beyond the intersection and a load-bearing tape is connected to each of the overlapping second profile sections and extends beyond the intersection.

4. The fuselage component according to claim 1 , wherein the stiffening structure is formed at least in regions with a plurality of layers lying one on top of another of shaped parts, wherein the profile edges of adjacent shaped parts of a respective layer overlap, and wherein a respective load-bearing tape is arranged between two adjacent layers, the load-bearing tape extending on the profile edges beyond the intersection.

5. The fuselage component according to claim 1 , wherein the stiffening structure has a flat covering layer composed of a fiber composite material, wherein the covering layer lies against the shaped parts and has recesses in a region of the intersections.

6. The fuselage component according to claim 1 , comprising:
a foam core which is arranged between the stiffening profiles and the shell part.

7. The fuselage component according to claim 1 , comprising:
a connection structure which is connected to one of the stiffening profiles and has a tab projecting from the stiffening profile.

8. The fuselage component according to claim 1 , comprising:
a connecting strip which is connected to the inner surface of the shell part, extends along a circumferential edge of the shell part and projects above the latter.

9. The fuselage component according to claim 1 , comprising:
a profile coupling structure which is connected to one of the stiffening profiles and protrudes beyond an end of the respective stiffening profile with respect to a longitudinal extent of the respective stiffening profile.

10. An aircraft comprising a fuselage which has at least one fuselage component according to claim 1 .

11. A method for producing a fuselage component, comprising:
Forming a stiffening structure from a multiplicity of shaped parts composed of a fiber composite material and each having a flat base section and a step-shaped profile edge, wherein the profile edge extends in an encircling manner around the base section, wherein the profile edge of each of the shaped parts comprises an interruption in a region of an interruption corner, and wherein the shaped parts are arranged such that the profile edges overlap and form stiffening profiles intersecting at an intersection in a region of an intersection corner;
placing an inner surface of a shell part of flat extent and composed of a fiber composite material onto the base sections of the shaped parts of the stiffening structure; and
connecting the shell part and the stiffening structure.

12. The method according to claim 11 , wherein a load-bearing tape is connected to each stiffening profile and extends beyond the intersection.

13. The method according to claim 11 , wherein the base sections of the shaped parts are of rectangular design, wherein the profile edge has two mutually opposite first profile sections which extend in a first direction, and two mutually opposite second profile sections which extend between the first profile sections in a second direction, wherein the first profile sections of in each case two shaped parts are arranged overlapping such that they form a first stiffening profile extending in the first direction, wherein the second profile sections of in each case two shaped parts are arranged overlapping such that they form a second stiffening profile which extends in the second direction and intersects the first stiffening profile at the intersection, and wherein load-bearing tapes composed of a fiber composite material and each extending beyond the intersections are connected to the first profile sections and to the second profile sections.

14. The method according to claim 11 , wherein, for supporting the stiffening structure, a foam core is arranged between the stiffening profiles and the shell part.

15. The method according to claim 11 , wherein the shaped parts are arranged as semi-finished fiber products on the shell part and, following the arrangement, are infiltrated with a matrix material.

16. The method according to claim 11 , wherein the shaped parts are arranged as semi-finished products composed of a fiber composite material, which has reinforcing fibers embedded in a matrix material, on the shell part.

Assignees

• Premium Aerotec Gmbh

Inventors

• Kuntz Julian
• Geipel Thomas

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B64C1/08

  Geodetic or other open-frame structures · CPC title

• B64C1/12 Primary

  Construction or attachment of skin panels · CPC title

• B29D99/0014 Primary

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B29L2031/3082

  Fuselages · CPC title