System and method for mounting aircraft system components in the crown area of an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F16L-003/26
B64C-001/06
B64D-011/00
B64F-005/00
B64C-001/00
출원번호
US-0444098
(2014-07-28)
등록번호
US-9644765
(2017-05-09)
발명자
/ 주소
Breuer, Matthias
Tuan, Wei-Chung
Klepka, Frank
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Greer, Burns & Crain Ltd.
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
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
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.
대표청구항▼
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; anda bridging el
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; anda 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, andwherein 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; anda 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, andwherein 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; andconnecting 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 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,the method further comprising:providing a plurality of cable ducts on at least the first longitudinal carrier element, the plurality of cable ducts 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;arranging electrical lines in the plurality of cable ducts;mounting the system 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 elements extend substantially parallel to a longitudinal axis of the aircraft. 15. The method according to claim 14, wherein, before the system is mounted in the crown area of an aircraft, at least one aircraft system component which is not constructed in the form of an electrical line, is fastened to the bridging element, said aircraft system component being fastened to the bridging element in 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. 16. The method according to claim 15, wherein the system is positioned, when the at least one aircraft system component is mounted on the bridging element, in such a way that said aircraft system component can be fastened to said bridging element from above, and the system, with the aircraft system component fastened to said bridging element, is rotated, prior to being mounted in the crown area of an aircraft, into a final mounting position in which the longitudinal carrier elements extend from the bridging element towards a floor of an aircraft cabin. 17. The method according to claim 14, wherein at least one electrical line is disposed in a cable duct which is disposed on the bridging element, in the region of a surface of said bridging element that faces away from the longitudinal carrier elements. 18. The method according to claim 14, wherein at least one electrical line is fastened by a clamping device which is disposed in a cable duct provided on at least one of the first and the second longitudinal carrier elements. 19. The method according to claim 14, wherein at least one electrical line is fastened by a clamping device which is disposed in the cable duct provided on the bridging element.
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이 특허에 인용된 특허 (10)
Young, David A.; Fraker, Richard; Brauer, R. Klaus; Guard, Peter S., Aircraft archway architecture.
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