# US 8,770,519 B2 · Structural component of an aircraft or spacecraft and a fuselage component arrangement of an aircraft or spacecraft

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- Number: US 8,770,519 B2
- Document ID: US8770519B2
- Status: Granted
- Kind: B2
- Application number: 13/113,572
- Filed: 2011-05-23
- Published: 2011-11-24
- Granted: 2014-07-08
- Earliest claimed: 2008-11-25
- Assignees: Airbus Operations GmbH
- Applicants: Claus-Peter Gross
- Inventors: Claus-Peter Gross
- Web page: https://patentgrep.com/patent/US8770519B2

## CPC

- B64C 1/065: {Spars}
- B64C 1/064: {Stringers; Longerons}
- B64C: AEROPLANES; HELICOPTERS

## Abstract

In the case of a structural component of an aircraft or spacecraft comprising a fuselage portion connection region for connecting to an associated fuselage portion and having a thermal expansion coefficient which is approximately matched to the associated fuselage portion; an inner connection region for connecting to an associated installation element and having a thermal expansion coefficient which is approximately matched to the associated installation element; and a separation region for connecting the fuselage portion connection region and the inner connection region, at least one of the regions has a high heat conduction resistance.

## Claims

### Claim 1

A fuselage component arrangement of an aircraft or spacecraft, comprising a fuselage portion and a one-piece structural component which comprises:
a fuselage portion connection region for connecting to the fuselage portion, which fuselage portion connection region has a thermal expansion coefficient which is approximately matched to the fuselage portion;
an inner connection region for connecting to an associated installation element, which inner connection region has a thermal expansion coefficient which is approximately matched to the associated installation element; and
a separation region for connecting the fuselage portion connection region and the inner connection region, wherein at least one of the regions has a material structure having a high heat conduction resistance,
wherein the fuselage portion connection region, the separation region and the inner connection region are formed in one piece with one another as the structural component, wherein the one piece structural component is as at least one of a metallic composite component or a fibre composite component,
wherein the one-piece structural component is formed as a composite component having a common matrix material that surrounds and impregnates each of the fuselage portion connection region, the separation region, and the inner connection region along substantially the entire length of the one-piece structural component, and wherein the separation region comprises a separation composite, having a high heat conduction resistance, and the matrix material, and
wherein a fuselage portion composite of the fuselage portion connection region and an inner composite of the inner connection region differ from the separation composite in terms of material, thermal expansion coefficient, and heat conduction resistance.

### Claim 2 (depends on 1)

The fuselage component arrangement according to claim 1, wherein the separation composite is formed as glass cloth.

### Claim 3 (depends on 1)

The fuselage component arrangement according to claim 1, wherein the fuselage portion connection region comprises a fuselage portion composite, made of a material corresponding to the fuselage portion, and the matrix material.

### Claim 4 (depends on 3)

The fuselage component arrangement according to claim 3, wherein the fuselage portion composite comprises the same composite material as the fuselage portion if the fuselage portion consists of a composite material.

### Claim 5 (depends on 3)

The fuselage component arrangement according to claim 3, wherein the fuselage portion comprises a metallic material, and wherein the fuselage portion composite comprises metal foils.

### Claim 6 (depends on 1)

The fuselage component arrangement according to claim 1, wherein the inner connection region comprises an inner composite, having a thermal expansion coefficient which is approximately matched to the associated installation element, and the matrix material.