Component arrangement on an aircraft structure, and a method for the installation of a component into an aircraft structure
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/14
B64D-043/00
B64D-043/02
출원번호
US-0003004
(2012-02-29)
등록번호
US-9493247
(2016-11-15)
우선권정보
DE-10 2011 005 355 (2011-03-10)
국제출원번호
PCT/EP2012/053453
(2012-02-29)
§371/§102 date
20131111
(20131111)
국제공개번호
WO2012/119906
(2012-09-13)
발명자
/ 주소
Reye, Volker
Tacke, Stefan
Billard, Cyrille
Streit, Kai
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Greer, Burns & Crain Ltd.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one comp
A component arrangement on an aircraft structure, in particular on a fuselage structure of an aircraft, with at least one mounting structure connected with the aircraft structure, and at least one component to be assigned to the aircraft structure, in particular a measuring device. At least one component carrier is provided to receive the component to be mounted, wherein the component carrier is connected with the mounting structure, and an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure. Also a method for the installation of a component into an aircraft structure with a mounting structure including the step of connecting the component with the mounting structure via a component carrier, so that an outer surface of the component carrier, facing away from the component, extends approximately flush with an outer surface of the aircraft structure.
대표청구항▼
1. A component arrangement on an aircraft structure, comprising: at least one mounting structure connected with the aircraft structure,at least one component configured to be mounted to the aircraft structure, andat least one component carrier for the reception of the component to be mounted,wherein
1. A component arrangement on an aircraft structure, comprising: at least one mounting structure connected with the aircraft structure,at least one component configured to be mounted to the aircraft structure, andat least one component carrier for the reception of the component to be mounted,wherein the component carrier is configured as a one-piece aerodynamic plate and wherein the installation of the component takes place directly on the aerodynamic plate,the component carrier being connected with the mounting structure, wherein the component carrier is inserted into a central receptacle of the round, approximately ring-shaped mounting structure from an inner side of the aircraft, wherein a supporting surface of a ring-shaped collar of the component carrier abuts against a seating face of a flange of the mounting structure, wherein the supporting surface is facing away from the inner side of the aircraft and the seating face is facing towards the inner side of the aircraft andan outer surface of the component carrier, facing away from the component, extending approximately flush with an outer surface of the aircraft structure. 2. The component arrangement according to claim 1, wherein said aircraft structure comprises a fuselage structure of an aircraft. 3. The component arrangement according to claim 1, wherein said component comprises a measuring device. 4. The component arrangement in accordance with claim 1, wherein the mounting structure is connected with an inner surface of the aircraft structure. 5. The component arrangement in accordance with claim 1, wherein the component carrier has a receiving section for the reception of a projection of the component to be mounted. 6. The component arrangement in accordance with claim 5, wherein the receiving section has an abutment face, facing towards the component, which can be brought into abutment against a flange face of the component. 7. The component arrangement in accordance with claim 6, wherein at least one seal is arranged in a ring shaped groove of the abutment face. 8. The component arrangement in accordance with claim 7, wherein said at least one seal comprises a sealing ring. 9. The component arrangement in accordance with claim 5, wherein an end face of the projection of the component, via at least one thermally effective seal which thermally couples the component and the component carrier, abuts against a contact face of the component carrier. 10. The component arrangement in accordance with claim 1, wherein a mounting web of the component carrier is approximately cup-shaped in design and the mounting structure is approximately ring-shaped, the component carrier being inserted in the mounting structure. 11. The component arrangement in accordance with claim 1, wherein a supporting surface of the component carrier abuts against a seating face of the mounting structure. 12. The component arrangement in accordance with claim 1, wherein the component carrier has an approximately L-shaped flange region with a ring-shaped collar, which is connected with the mounting structure. 13. The component arrangement in accordance with claim 1, wherein the at least one component is a pressure measuring device. 14. The component arrangement in accordance with claim 13, wherein the pressure measuring device is a static pressure load cell. 15. A method for the installation of a component into an aircraft structure, comprising the steps: mounting a mounting structure on the aircraft structure,connecting the component with the mounting structure via a component carrier, wherein the component carrier is designed as a one-piece aerodynamic plate and wherein the installation of the component takes place directly on the aerodynamic plate,with an outer surface of the component carrier, facing away from the component, extending approximately flush with an outer surface of the aircraft structure, wherein the component carrier is inserted into a central receptacle of the round, approximately ring-shaped mounting structure from an inner side of the aircraft, wherein a supporting surface of a ring-shaped collar of the component carrier abuts against a seating face of a flange of the mounting structure, wherein the supporting surface is facing away from the inner side of the aircraft and the seating face is facing towards the inner side of the aircraft. 16. The method according to claim 15, wherein the component is a measuring device on a fuselage structure of an aircraft. 17. The method in accordance with claim 15, including the further step of connecting the mounting structure with the aircraft structure such that a seating face for the component carrier has a defined clearance from the outer surface of the aircraft structure.
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이 특허에 인용된 특허 (7)
Sobotta, Gerald; Bosch, Dieter, Device for measuring pressure, sound and vibration and method of analyzing flow on surfaces of structural parts.
Jean-Marc Bourgon FR; Serge Bayonne FR; Bruno Chauveau FR, Device for pressure tapping and procedure for setting it on a fuselage panel of an aircraft.
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