Structural component, method for producing a structural component, pressure fuselage for a vehicle comprising a structural component

Patent metadata

Field	Value
Publication number	US-10549488-B2
Application number	US-201715454068-A
Country	US
Kind code	B2
Filing date	Mar 9, 2017
Priority date	Mar 10, 2016
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A structural component has a main body formed of a fibre composite material, a plurality of first reinforcement parts and a plurality of second reinforcement parts, wherein the main body is formed as a domed body having a peripheral edge and a vertex, wherein the first reinforcement parts are connected to the main body and in each case have a concave curvature course in relation to a first plane, and wherein the second reinforcement parts are connected to the main body and also have a concave curvature course in each case in relation to a second plane.

First claim

The invention claimed is:

1. A structural component configured for use in a pressure fuselage of a vehicle comprising:
a main body formed of a fibre composite material, a plurality of first reinforcement parts and a plurality of second reinforcement parts,
wherein the main body is formed as a domed body having a peripheral edge and a vertex,
wherein each of the plurality of first reinforcement parts is connected to the main body and extends between corresponding two points of a corresponding first pair of points located on the peripheral edge so as to be spaced apart in a component peripheral direction in such a way that each of the plurality of first reinforcement parts has a concave curvature course in relation to a first plane which extends in a first curvature direction produced at the vertex and through the curvature centre point thereof and of the vertex, each of the concave curvature courses of the plurality of first reinforcement parts extending toward the first plane, and
wherein each of the plurality of second reinforcement parts is connected to the main body and extends between corresponding two points of a corresponding second pair of points located in the peripheral edge so as to be spaced apart in the component peripheral direction in such a way that each of the plurality of second reinforcement parts has a concave curvature course in relation to a second plane which extends in a second curvature direction produced at the vertex and through the curvature centre point thereof and of the vertex, each of the concave curvature courses of the plurality of second reinforcement parts extending toward the second plane.

2. The structural component of claim 1 , wherein a first vertex reinforcement part, which is formed by one of the plurality of first reinforcement parts, extends through the vertex of the main body, and a second vertex reinforcement part, which is formed by one of the plurality of second reinforcement parts, extends though the vertex of the main body.

3. The structural component of claim 1 , wherein the first curvature direction is the first main curvature direction produced at the vertex, and the second curvature direction is the second main curvature direction produced at the vertex.

4. The structural component of claim 1 , wherein the first and the second reinforcement parts in each case have a concave curvature course in relation to the first and the second plane in such a way that, in each case, two of a plurality of fields of the structural component which are in each case delimited by two second and two first reinforcement parts, in each case have surface areas which deviate from one another by at most 15 percent.

5. The structural component of claim 1 , wherein the first and the second reinforcement parts in each case have a concave curvature course in relation to the first and the second plane in such a way that, in each case, two of a plurality of fields of the structural component which are in each case delimited by two second and two first reinforcement parts, in each case have surface areas which deviate from one another by at most 10 percent.

6. The structural component of claim 1 , wherein the first and the second reinforcement parts in each case have a concave curvature course in relation to the first and the second plane in such a way that, in each case, two of a plurality of fields of the structural component which are in each case delimited by two second and two first reinforcement parts, in each case have surface areas which deviate from one another by at most 5 percent.

7. The structural component of claim 1 , wherein each of the pluralities of first and the second reinforcement parts is formed by at least one fibre composite strip.

8. The structural component of claim 1 , wherein the main body has at least two fibre composite material layers.

9. The structural component of claim 8 , wherein the fibre composite material layers of the main body are in each case formed by a plurality of fibre composite strips extending in a strip longitudinal direction, wherein the strip longitudinal direction of the fibre composite strips of a first fibre composite material layer extends obliquely to the strip longitudinal direction of the fibre composite strips of an adjacent fibre composite layer.

10. The structural component of claim 8 , wherein the pluralities of first and second reinforcement parts are embedded between two fibre composite layers at least in part.

11. The structural component of claim 1 , wherein the pluralities of first and second reinforcement parts are arranged on a surface of the main body.

12. The structural component of claim 1 , wherein the structural component has a peripheral terminal part which extends along the peripheral edge of the main body and is connected thereto in such a way that the peripheral edge of the main body is located within the peripheral terminal part in relation to a width thereof, such the peripheral terminal part forms an edge of the structural component.

13. A method for producing a structural component configured for use in a pressure fuselage of a vehicle, the method comprising:
forming a semi-finished product arrangement by
laying a fibre composite material semi-finished product, which comprises a fibre layer pre-impregnated with a matrix material, on a contour surface of a tool part, the surface course of which contour surface is such that the fibre composite material semi-finished product forms a domed main body arrangement having a peripheral edge and a vertex,
laying a plurality of first reinforcement parts on the fibre composite material in such a way that each of the plurality of first parts extends between corresponding two points of a corresponding first pair of points located in the peripheral edge so as to be spaced apart in a component peripheral direction in such a way that each of the plurality of first reinforcement parts has a concave curvature course in relation to a first plane which extends in a first curvature direction produced at the vertex and through the curvature centre point thereof, each of the concave curvature courses of the plurality of first reinforcement parts extending toward the first plane, and
laying a plurality of second reinforcement parts on the fibre composite material in such a way that each of the plurality of second reinforcement parts extends between corresponding two points of a corresponding second pair of points located in the peripheral edge so as to be spaced apart in a component peripheral direction in such a way that each of the plurality of second reinforcement parts has a concave curvature course in relation to a second plane which extends in a second curvature direction produced at the vertex and through the curvature centre point thereof, each of the concave curvature courses of the plurality of second reinforcement parts extending toward the second plane; and
heating the semi-finished product arrangement under the application of pressure, and thereby hardening the matrix material to form a main body from the fibre composite semi-finished product and to connect the first and second reinforcement parts to the main body.

14. The method of claim 13 , wherein, when forming the semi-finished product arrangement, after laying on the plurality of second reinforcement parts a further fibre composite material semi-finished product is laid on.

15. The method of claim 13 , wherein the fibre composite material semi-finished product is laid on by consecutively arranging at least two fibre composite material layers on the contour surface of the tool part.

16. The method of claim 15 , wher

Assignees

• Premium Aerotec Gmbh

Inventors

• Pfau Reinald
• Scholler Jochen
• Hoerger Bernhard
• Drexl Thomas

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B64C1/10 Primary

  Bulkheads · CPC title

• B32B2260/023

  Two or more layers · CPC title

• B32B37/06

  characterised by the heating method · CPC title

• B32B5/12

  characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other} · CPC title