Component, reinforcement member, structural arrangement, aircraft or spacecraft and method
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-005/10
B29C-070/20
D03D-013/00
B64C-001/00
B29C-070/22
B29C-070/86
출원번호
US-0649203
(2012-10-11)
등록번호
US-8833697
(2014-09-16)
우선권정보
DE-10 2011 084 433 (2011-10-13)
발명자
/ 주소
Seack, Oliver
Bruns, Alexander
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
3인용 특허 :
23
초록▼
A component for connecting structures to intersection regions of said component is disclosed, particularly for an aircraft or spacecraft, including a coupling element, including a first fiber which wraps around the coupling element so that the first fiber extends in a first plane in front of the cou
A component for connecting structures to intersection regions of said component is disclosed, particularly for an aircraft or spacecraft, including a coupling element, including a first fiber which wraps around the coupling element so that the first fiber extends in a first plane in front of the coupling element and in a second plane behind the coupling element, the first and second planes intersecting, and including a second fiber which wraps around the coupling element so that the second fiber extends in a third plane in front of the coupling element and in a fourth plane behind the coupling element, the third and fourth planes intersecting, and with the first fiber portions of the first and second fibers crossing over in a first region and the second fiber portions of the first and second fibers crossing over in a second region.
대표청구항▼
1. A component for connecting structures to intersection regions of said component, for an aircraft or spacecraft, comprising a coupling element, comprising a first fibre which wraps around the coupling element in such a way that the first fibre extends, with a first fibre portion, in a first plane
1. A component for connecting structures to intersection regions of said component, for an aircraft or spacecraft, comprising a coupling element, comprising a first fibre which wraps around the coupling element in such a way that the first fibre extends, with a first fibre portion, in a first plane in front of the coupling element and, with a second fibre portion, in a second plane behind the coupling element, the first and second planes intersecting, and comprising a second fibre which wraps around the coupling element in such a way that the second fibre extends, with a first fibre portion, in a third plane in front of the coupling element and, with a second fibre portion, in a fourth plane behind the coupling element, the third and fourth planes intersecting, the first fibre portions of the first and second fibres crossing over in a first region and the second fibre portions of the first and second fibres crossing over in a second region. 2. The component according to claim 1, wherein the first and second planes are arranged substantially perpendicular to one another or the third and fourth planes are arranged substantially perpendicular to one another. 3. The component according to claim 1, wherein the coupling element comprises one or more fibres which are interwoven, the one or more fibres extending in a direction perpendicular to a plane in which the first or second fibre wraps around the coupling element. 4. The component according to claim 3, wherein the one or more fibres comprise glass or carbon or are provided with a thermoplastic or thermosetting matrix. 5. The component according to claim 3, wherein the coupling element is formed, in the shape of a rod from a monolithic material, wherein the monolithic material is aluminium or titanium. 6. The component according to claim 1, wherein the coupling element has a rounded, circular cross-section in a plane in which the first or second fibre wraps around the coupling element. 7. The component according to claim 1, wherein a multitude of first fibres, which form a plurality of first fibre strands and a multitude of second fibres are provided which form a plurality of second fibre strands which are arranged so as to alternate with the first fibre strands in a direction perpendicular to a plane in which a respective first or second fibre wraps around the coupling element. 8. The component according to claim 7, wherein the first fibre strands are interwoven with third fibre strands and the second fibre strands are interwoven with fourth fibre strands, for example, fifth fibre strands further being interwoven with the third fibre strands and forming a first closed passage together with the first fibre strands or sixth fibre strands being interwoven with the fourth fibre strands and forming a second closed passage together with the second fibre strands, the coupling element extending through the first and second passages. 9. A reinforcement member for connecting structures to intersection regions of said member for an aircraft or spacecraft, comprising an embedding part and comprising a component according to claim 1 which is embedded into the embedding part. 10. Structural arrangement, for an aircraft or spacecraft, comprising a first structure, comprising a second structure which forms an intersection region together with the first structure, andcomprising the component according to claim 1 which interconnects the first and second structures in the intersection region. 11. The structural arrangement according to claim 10, wherein the first structure is formed as a box structure of an aerofoil or control surface or a control flap, the first fibre portion of the first fibre of the component being connected to a first wall portion of the box structure or the second fibre portion of the second fibre being connected to a second wall portion of the box structure, the second structure being configured as an internal web inside and an external web outside the box structure, the first fibre portion of the second fibre of the component being connected to the internal web or the second fibre portion of the first fibre of the component being connected to the external web, the external web comprising an eye for attaching an adjusting member selected from the group consisting of a flap carriage, a lever or a coupling rod. 12. The structural arrangement according to claim 11, wherein an adjusting member arranged on an aerofoil or control surface engages in the eye of the external web, the adjusting member being configured as a flap carriage which is displaceably arranged on the aerofoil or control surface and is in engagement with the eye. 13. An aircraft or spacecraft having a structural arrangement according to claim 10. 14. A method for producing a component according to claim 1, having the following steps: placing a first fibre around a first coupling element in such a way that the first fibre extends, with a first fibre portion, in a first plane in front of the coupling element together and, with a second fibre portion, in a second plane behind the coupling element, the first and second planes intersecting,placing a second fibre around a second coupling element in such a way that the second fibre extends, with a first fibre portion, in a third plane in front of the coupling element and, with a second fibre portion, in a fourth plane behind the coupling element, the third and fourth planes intersecting,removing the first and second coupling elements,superposing the first fibre with the second fibre in such a way that the first fibre portions of the first and second fibres intersect in a first region and the second fibre portions intersect in a second region and therefore form a closed passage for a third coupling element,inserting the third coupling element through the closed passage. fibre portions of the first and second fibres intersect in a first region and the second fibre portions intersect in a second region and therefore form a closed passage for a third coupling element,inserting the third coupling element through the closed passage. 15. Method according to claim 14, wherein a first woven fabric having a multitude of first fibres and a second woven fabric having a multitude of second fibres are provided, the first coupling element being pushed into a compartment instead of the weft thread when weaving the first woven fabric and the second coupling element being pushed into a compartment when weaving the second woven fabric.
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이 특허에 인용된 특허 (23)
Loyek Ernie F. (Sparks NV), Composite cruciform structure for joining intersecting structural members of an airframe and the like.
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