Aircraft structural component

Patent metadata

Field	Value
Publication number	US-10377461-B2
Application number	US-201514747707-A
Country	US
Kind code	B2
Filing date	Jun 23, 2015
Priority date	Jul 4, 2014
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.

First claim

The invention claimed is:

1. An aircraft structural component, comprising:
a skin element, which includes an inner surface and an outer surface;
a multitude of transverse stiffening elements, which lie spaced apart from each other against the inner surface of the skin element; and
a multitude of longitudinal stiffening elements, which lie spaced apart from each other and transverse to the transverse stiffening elements against the inner surface of the skin element;
wherein the skin element includes a multitude of skin sections, each of which is defined between two neighboring transverse stiffening elements and two neighboring longitudinal stiffening elements,
wherein between a first and a second transverse stiffening element and between a first and a second longitudinal stiffening element, a first skin section is defined,
wherein, in the first skin section on the inner surface of the skin element a first applied reinforcement is mounted,
wherein the first applied reinforcement includes a core layer lying against the inner surface of the skin element and having a circumferential contour line on the inner surface of the skin element,
wherein the first applied reinforcement includes a face sheet surrounding the core layer on a side of the core layer which faces away from the skin element, which face sheet is directly attached to the skin element along the circumferential contour line of the core layer, such that the core layer is entirely enclosed between the face sheet and the inner surface of the skin element,
wherein the face sheet is formed integrally with either one of or both of the first longitudinal stiffening element and the second longitudinal stiffening element, and
wherein the circumferential contour line of the core layer has a shape which is lenticular, elliptical or circular when viewed perpendicular to the inner surface.

2. The aircraft structural component according to claim 1 , wherein the first applied reinforcement extends from the first transverse stiffening element to the second transverse stiffening element or from the first longitudinal stiffening element to the second longitudinal stiffening element.

3. The aircraft structural component according to claim 1 , wherein when viewed in a cross-section perpendicular to the longitudinal stiffening elements, a surface of the core layer has, on the side facing away from the skin element, a lenticular curve.

4. The aircraft structural component according to claim 1 , wherein a third transverse stiffening element is provided next to the second transverse stiffening element,
wherein between the second and the third transverse stiffening elements and also between the first and the second longitudinal stiffening elements, a second skin section is defined,
wherein in the second skin section on the inner surface of the skin element, a second applied reinforcement is mounted.

5. The aircraft structural component according to claim 4 , wherein the face sheet of the first applied reinforcement is formed integrally with a face sheet of the second applied reinforcement.

6. The aircraft structural component according to claim 1 , wherein a third longitudinal stiffening element is provided next to the second longitudinal stiffening element,
wherein between the first and the second transverse stiffening elements and the second and the third longitudinal stiffening elements, a second skin section is defined,
wherein in the second skin section on the inner surface of the skin element, a second applied reinforcement is mounted.

7. The aircraft structural component according to claim 6 , wherein a third transverse stiffening element is provided next to the second transverse stiffening element,
wherein between the second and the third transverse stiffening element and the first and the third longitudinal stiffening element, a third skin section is defined,
wherein in the third skin section on the inner surface of the skin element, a third applied reinforcement is mounted, which extends from the first to the third longitudinal stiffening element.

8. The aircraft structural component according to claim 6 , wherein an additional transverse stiffening element is provided next to the first transverse stiffening element on a side of the first transverse stiffening element opposite the second transverse stiffening element,
wherein between the additional transverse stiffening element and the first transverse stiffening element and also between the first and the second longitudinal stiffening elements, an additional longitudinal stiffening element is provided,
wherein between the additional transverse stiffening element and the first transverse stiffening element and also between the first longitudinal stiffening element and the additional longitudinal stiffening element, a first additional skin section is defined,
wherein between the additional transverse stiffening element and the first transverse stiffening element and also between the additional longitudinal stiffening element and the second longitudinal stiffening element, a second additional skin section is defined, and
wherein in the first and second additional skin sections on the inner surface of the skin element, no applied reinforcement is mounted.

9. The aircraft structural component according to claim 1 , wherein the circumferential contour line of the core layer has, on a side facing away from the inner surface, a shape which is semi-lenticular when viewed in cross section perpendicular to both the longitudinal and the transverse stiffening elements.

Assignees

• Airbus Operations Gmbh

Inventors

• Jörn Paul
• Zahlen Pierre
• Müller Markus
• Zuardy Ichwan
• Hanske Claus

Classifications

• B64C1/064

  Stringers; Longerons · CPC title

• B64C1/12 Primary

  Construction or attachment of skin panels · CPC title

• B64C1/068

  Fuselage sections · CPC title