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Method for through-repair of a composite structure comprising three skins and two core layers

A composite structure, skin technology, used in home appliances, other home appliances, lamination, etc.

Active Publication Date: 2010-05-19
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the usual method, the repaired part of the structure is enclosed in a vacuum bag forming a cavity in which a vacuum is applied to suck excess resin and evacuate air in order to facilitate release from the mold, but not always Emissions are achieved in a satisfactory manner

Method used

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  • Method for through-repair of a composite structure comprising three skins and two core layers
  • Method for through-repair of a composite structure comprising three skins and two core layers
  • Method for through-repair of a composite structure comprising three skins and two core layers

Examples

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Embodiment Construction

[0012] figure 1 The structure includes an inner structure 1 and two opposite outer skins 2 and 3, wherein the inner structure 1 is embedded between the two skins 2 and 3 by bonding. The outer skins 2 and 3 generally consist of several layers of plissé polymers which are successively laid up and subsequently hardened. The inner structure 1 comprises two honeycomb cores 16 and 19 generally composed of a honeycomb structure whose cells extend from one outer skin 2 to the other 3 . These two core layers are separated by a third skin, which is an intermediate skin 17 of the same kind as the outer skins 2 and 3 . The repair consists of replacing a part of the structure with a new part comprising: a new skin part 6 extending the outer skin 2 on the external sides of the structure, a new first core extending the first core layer 16 layer section 20, a new middle skin section 21 extending the middle skin 17, a new second core section 22 extending the second core layer 19, and a new s...

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PUM

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Abstract

The invention concerns a method whereby repair portions (6, 20, 21, 22 and 23), set through two core layers (16, 19), for example with honeycomb structure and three polymer skins (2, 3, 17) two of which being outer skins and the third an intermediate skin interposed between the two core layers to provide a composite structure, are installed and the polymer is vacuum hardened. An backing block (8)is pressed on one of the skins (2) to ensure a good appearance and a good surface quality. The invention is characterized in that vents (24) are provided through the intermediate skin (21) and optionally through the skin (2) receiving the anvil form for proper degassing of the underlying cellular core (20).

Description

technical field [0001] The present invention relates to a method for the overhaul of so-called double-sandwich composite structures, wherein the double-sandwich composite structure comprises two honeycomb-shaped inner core layers between a pair of outer skins (peau), and The middle skin in between. Background technique [0002] Composite structures are found in a variety of devices, especially in transportation, railroad, marine, or aeronautical machinery; for example, on the hulls of ships or on the outer aeroshells, leading edges of airfoils, aircraft ailerons, and radar antennas cover. The use of an intermediate skin provides certain advantages of radio penetrability. [0003] This structure is often damaged to the extent that it needs to be replaced locally. A new skin and core section is joined at the repair location by lengthening the intact section and the new skin section is hardened. In order to ensure a sufficiently smooth repair surface on the outside of the s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C73/04B29C73/32B32B43/00B32B3/12B64F5/00H01Q1/42
CPCB29L2031/3076B29L2031/3456B29C73/32B32B43/00B29C2073/268B29C73/04B29L2031/608B32B2305/024
Inventor 克里斯托夫·拜尔努什让-克洛德·马蒂雅克·富尼耶
Owner AIRBUS OPERATIONS (SAS)