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Joint attaching structural element to composite part and aircraft including the joint

A technology of composite parts and structural elements, applied in aircraft parts, aircraft indicating devices, aircraft lighting protectors, etc., can solve problems such as expensive, expensive solutions, and increased weight of aircraft

Inactive Publication Date: 2013-07-24
EADS飞机设计有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, these known solutions have the problem of adding weight to the overall weight of the aircraft
Besides that, these solutions are expensive and require strong repairability revisions, which are also expensive
[0005] Especially in the case where the connected aircraft elements are metallic and made of composite materials, and the elements need to be fire-resistant and subjected to high loads, especially high vertical loads, the use of established Known solutions are not suitable due to their high cost and weight

Method used

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  • Joint attaching structural element to composite part and aircraft including the joint
  • Joint attaching structural element to composite part and aircraft including the joint
  • Joint attaching structural element to composite part and aircraft including the joint

Examples

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Embodiment Construction

[0016] In some parts of the aircraft structure, such as figure 1 As shown, it is necessary to connect a structural element 10 (typically metallic) with an element or component 20 made of composite material. In some cases these structural elements 10 are subjected to high structural loads 30 from the aircraft. Typically, the structural element 10 is connected to the composite part 20 by metal attachments 40, typically rivets or bolts. In the event of a fire, the strength of the composite part 20 is greatly reduced, as it has been found that in composite structures subjected to high temperatures, the strength to forces (especially to vertical forces) is very critical, as figure 1 and figure 2 The same is the case in the prior art shown in .

[0017] It is common practice in the industry to protect structural elements 10 subjected to fire by the use of thermal lays or coatings comprising insulating materials of low thermal conductivity to reduce the temperature on the part be...

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PUM

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Abstract

Joint attaching a structural element (10) to a composite part (20) comprising a metallic attachment (40), this joint being subjected to a fire source on one of its sides, the fire side, the joint comprising a retaining device (50) locate at the side of the joint opposite to the fire side, the cold side, the retaining device (50) comprising a first surface (51) that is in contact with the metallic attachment (40), and a second surface (52) which is in contact with the composite part (20), the second surface (52) having a bigger area than the area of the first surface (51), the retaining device (50) being made of a material with a high thermal conductivity. The invention also refers to an aircraft comprising such a joint.

Description

technical field [0001] The present invention relates to a device for use in an aircraft, in particular to joints for attaching structural elements and composite parts in an aircraft such that these joints bear structural loads and It is fire resistant. Background technique [0002] Currently, composite materials are being used more and more frequently in aircraft structures due to weight constraints in current aircraft designs. In some parts of aircraft structures, metal elements are joined with elements made of composite materials. In some cases, these joints are subjected to high structural loads from the aircraft. In the event of a fire on these joints, the strength of the composite element is greatly reduced, since it has been found that strength against forces, especially vertical forces, is critical in composite structures subjected to high temperatures. Thus, in said case, a high strength reduction in the composite material element would cause a detachment of the m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/00F16B1/00
CPCB64C1/06B64D45/00B64D45/02
Inventor 费尔南多·坎波卡巴莱罗吕本·阿拉戈内塞斯曼索
Owner EADS飞机设计有限公司
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