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A composite sandwich structure

A composite foam and surface layer technology, applied in the direction of upper structure, upper structure sub-assembly, synthetic resin layered products, etc., can solve the problems of no invention and use, low compressive strength, rigidity and easy plastic deformation, etc.

Active Publication Date: 2018-04-17
FERGUSSONS ADVANCED COMPOSITE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it has two major disadvantages: its stiffness (and strength) to weight ratio and its susceptibility to plastic deformation
The low-density cores with correspondingly low compressive strengths present in the above-mentioned panels suffer localized indentation failures, which lead to them having to be taken out of service
It is for this reason that the above-mentioned inventions have not been found to be in use at present on bulk shipments

Method used

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  • A composite sandwich structure
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Examples

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Embodiment Construction

[0056] figure 1 A composite sandwich base panel is shown comprising an upper surface layer 1 and a lower surface layer 5 sandwiching a composite foam core 3 . On both sides of the core are barrier layers 2 and 4 . The entire panel is then surrounded by a number of outer edge pieces (not shown). There may be variations in the local material composition of the composite core 3 and / or there may be variations in the local geometry of the peripheral regions for the region where the edge parts are to be attached to the panels. A wear resistant layer 6 may be bonded to the lower surface layer 5 .

[0057] Depending on the manufacturing process used, some embodiments of the present invention include a porous structure incorporated into the syntactic foam 3 . FIG. 2A is a horizontal section of the hexagonal cellular structure 12 incorporated in the syntactic foam core 3 , and FIG. 2B is a vertical section of the hexagonal cellular structure 12 incorporated in the syntactic foam core...

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Abstract

The invention relates to a composite sandwich base panel for a Unit Load Device. The panel comprises an upper surface layer comprising fibre reinforcement material, a lower surface layer comprising fibre reinforcement material, and a central core section where at least the majority comprises a plurality of particles bound in a matrix material. The upper surface layer and lower surface layer are provided with a matrix material to bind them to the central core section.

Description

technical field [0001] The present invention relates to a lightweight composite sandwich base panel, in particular a lightweight composite sandwich base panel for use as part of a Unit Load Device. Background technique [0002] Air cargo is typically transported in or on an unit load unit which may be in the form of a container or a pallet. As with all aspects of the aviation industry, weight reduction is a key priority as it equates to improved fuel efficiency and lower operating costs. Most unit load units are currently made of high-strength aluminum alloys, a holdover from the first-generation designs of the 1960s. Aluminum alloys can provide the right combination of cost, density and manufacturability. However, it has two major disadvantages: its stiffness (and strength) to weight ratio and its susceptibility to plastic deformation. [0003] Composite materials, especially composite sandwich structures, are known to have a high stiffness (and strength) to weight ratio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B3/12B32B5/02B32B5/12B32B5/14B32B5/18B32B5/24B32B5/28B32B7/04B32B27/04B32B27/38E04C2/20E04C2/24E04C2/36
CPCB32B3/12B32B5/02B32B5/024B32B5/12B32B5/14B32B5/142B32B5/18B32B5/245B32B5/28B32B7/04B32B27/04B32B27/38E04C2/205E04C2/243E04C2/365B32B2307/72B32B2307/558B32B2307/536B32B2307/546B32B2307/552B32B2262/101B32B2262/106B32B2266/04B32B2264/101B32B2264/102B32B2264/12B32B2260/023B32B2250/40B32B2250/03B32B2250/04B32B2250/05B32B2260/046B32B2260/025B32B2439/00B29C70/66B62D25/2054B65D19/0002B65D2519/00034B65D2519/00069B65D2519/00273B65D2519/00343B65D2519/00562B65D2519/00572B65D2519/00039B65D2519/00044B65D2519/00074B65D2519/00079B65D2519/00278B32B3/08B32B27/065B32B27/12B32B2377/00B32B2553/00B32B2266/0271B32B2266/08B32B2264/02B32B2305/08B32B2305/024B32B2305/022B32B2323/04B32B2307/71B32B2307/3065B32B2266/057B32B27/08B32B2605/18B65D19/0004B65D88/14
Inventor A·D·弗格森A·G·纽曼A·P·L·梅奥尔T·B·巴勒夫J·P·凯西T·王M-A·L·迪加斯图
Owner FERGUSSONS ADVANCED COMPOSITE TECH
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