System and method for mounting aircraft system components in the crown area of an aircraft

Patent metadata

Field	Value
Publication number	US-9644765-B2
Application number	US-201414444098-A
Country	US
Kind code	B2
Filing date	Jul 28, 2014
Priority date	Jan 30, 2012
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

A system for mounting aircraft system components in the crown area of an aircraft comprising a first longitudinal carrier element, a second longitudinal carrier element and a bridging element which connects the first longitudinal carrier element to the second longitudinal carrier element. The system is mountable in the crown area of an aircraft in such a way that the first and the second longitudinal carrier elements extend substantially parallel to the longitudinal axis of the aircraft. A plurality of cable ducts for accommodating electrical lines is provided on the first and/or the second longitudinal carrier elements.

First claim

The invention claimed is:

1. A system for mounting aircraft system components in the crown area of an aircraft, said system comprising:
a first longitudinal carrier element;
a second longitudinal carrier element disposed substantially parallel to and at a distance from said first longitudinal carrier element; and
a bridging element which connects the first longitudinal carrier element to the second longitudinal carrier element,
wherein the system is mountable in the crown area of an aircraft in such a way that a longitudinal axis of each of the first and the second longitudinal carrier element extend substantially parallel to a longitudinal axis of the aircraft, and
wherein a plurality of cable ducts for accommodating electrical lines is provided on at least one of the first and the second longitudinal carrier elements,
wherein the first longitudinal carrier element comprises a main body having a first main surface and a second main surface, the first and second main surfaces forming an outer appearance of the first longitudinal carrier element and extending substantially parallel to the longitudinal axis of the first longitudinal carrier element, the first main surface facing towards the second longitudinal carrier element and the second main surface facing away from said second longitudinal carrier element, cable ducts provided on the first longitudinal carrier element being disposed both in the region of the first main surface and in the region of the second main surface of the main body of the first longitudinal carrier element.

2. The system according to claim 1 , wherein the second longitudinal carrier element comprises a main body having a first main surface and a second main surface, the first and second main surfaces forming an outer appearance of the second longitudinal carrier element and extending substantially parallel to the longitudinal axis of the second longitudinal carrier element, the first main surface facing towards the first longitudinal carrier element and the second main surface facing away from said first longitudinal carrier element, cable ducts provided on the second longitudinal carrier element being disposed both in the region of the first main surface and in the region of the second main surface of the main body of the second longitudinal carrier element.

3. The system according to claim 1 , wherein at least some of the cable ducts provided on at least one of the first and the second longitudinal carrier elements are defined by separating elements which keep the electrical lines accommodated in the cable ducts at a predetermined distance from one another.

4. The system according to claim 3 , wherein the main body of the first longitudinal carrier element is shaped in such a way, and the separating elements of said first longitudinal carrier element are shaped and positioned in such a way, that the mounting of an electrical line in a cable duct of the first longitudinal carrier element, and the demounting of an electrical line from a cable duct of the first longitudinal carrier element, is not hindered by other electrical lines accommodated in the other cable ducts of said first longitudinal carrier element.

5. The system according to claim 3 , wherein the main body of the second longitudinal carrier element is shaped in such a way, and the separating elements of said second longitudinal carrier element are shaped and positioned in such a way, that the mounting of an electrical line in a cable duct of the second longitudinal carrier element, and the demounting of an electrical line from a cable duct of the second longitudinal carrier element, is not hindered by other electrical lines accommodated in the other cable ducts of said second longitudinal carrier element.

6. The system according to claim 1 , wherein at least one of the first and the second longitudinal carrier elements comprises an electromagnetically screening material.

7. The system according to claim 1 , wherein at least one of the first and the second longitudinal carrier elements has a layer made of an electrically conductive material, in particular of aluminum, which is applied to at least partial regions of a surface of said first longitudinal carrier element.

8. The system according to claim 1 , further comprising at least one component holder for fastening at least one aircraft system component which is not constructed in the form of an electrical line, to the bridging element, said component holder being adapted to fasten the aircraft system components to the bridging element at such a position that the mounting of said aircraft system component on said bridging element, and the demounting of said aircraft system component from said bridging element, is not hindered by the longitudinal carrier elements and electrical lines accommodated in the cable ducts of said longitudinal carrier elements.

9. The system according to claim 1 , wherein at least one cable duct for accommodating at least one electrical line is provided on the bridging element, said cable duct being disposed in the region of a surface of said bridging element that faces away from the longitudinal carrier elements, and the bridging element comprising an electromagnetically screening material.

10. The system according to claim 9 , wherein a clamping device is disposed in the cable duct provided on the bridging element.

11. The system according to claim 1 , wherein a clamping device is disposed in the cable ducts provided on at least one of the first and the second longitudinal carrier elements.

12. The system according to claim 1 , wherein at least one of the first and the second longitudinal carrier element has a layer made of an electrically conductive material, in particular of aluminum, which is applied to at least partial regions of a surface of said second longitudinal carrier element.

13. A system for mounting aircraft system components in the crown area of an aircraft, said system comprising:
a first longitudinal carrier element;
a second longitudinal carrier element; and
a bridging element which connects the first longitudinal carrier element to the second longitudinal carrier element,
wherein the system is mountable in the crown area of an aircraft in such a way that the first and the second longitudinal carrier element extend substantially parallel to a longitudinal axis of the aircraft, and
wherein a plurality of cable ducts for accommodating electrical lines is provided on at least one of the first and the second longitudinal carrier elements,
further comprising at least one structure holder for fastening the system to an aircraft structure element, said structure holder comprising a connecting element which is provided with a bore, and also a fastening arrangement, said fastening arrangement being intended to pass through the bore provided in the connecting element and also through a bore provided in the aircraft structure element, and said fastening arrangement comprising a pin which is accommodated in a sleeve comprising an elastically deformable material.

14. A method for mounting aircraft system components in the crown area of an aircraft, said method comprising the following steps:
providing a first longitudinal carrier element;
providing a second longitudinal carrier element disposed substantially parallel to and at a distance from said first longitudinal carrier element; and
connecting the first and the second longitudinal carrier element to a bridging element,
wherein the first longitudinal carrier element comprises a main body having a first main surface and a second main surface, the first and second main surfaces forming an outer appearance of the fir

Assignees

• Airbus Operations Gmbh

Inventors

• Breuer Matthias
• Tuan Wei-Chung
• Klepka Frank

Classifications

• B64D2011/0046

  Modular or preassembled units for creating cabin interior structures · CPC title

• Y10T29/49826

  Assembling or joining · CPC title

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• F16L3/26 Primary

  specially adapted for supporting the pipes all along their length, e.g. pipe channels or ducts · CPC title

• B64F5/0009

  Operations & Transport · mapped topic