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Aircraft side fairing

A technology for fairing panels and aircraft, applied in aircraft parts, fuselage, mechanical equipment, etc., can solve the problems of unfavorable insulation of sidewall panels, reduced aircraft performance, etc., and achieve the effects of reducing aircraft weight, improving heat insulation effect, and reducing thickness

Inactive Publication Date: 2009-07-08
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Its disadvantage is that due to the arrangement of the core material and the hollow space between the two covering layers, a special thermal conductivity of the material results, which in the case of a typical side rectifier has a value of approximately 0.06 W / mK Thermal conductivity
Extra weight also means reduced aircraft performance
In addition, the installation of additional insulation in the form of secondary insulation is not conducive to the production process of the side wall panels, requiring a separate manufacturing step

Method used

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  • Aircraft side fairing
  • Aircraft side fairing
  • Aircraft side fairing

Examples

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Embodiment Construction

[0036] In the drawings, unless otherwise stated, identical reference numerals designate identical or functionally identical components.

[0037] Figures 1 to 3 A cross-sectional view of a side fairing according to the prior art is shown for reference. according to figure 1 , provided with a core material for an aircraft side fairing comprising a first covering layer 1 and a second covering layer 2 with a core material 3 in the form of a hollow cavity between the layers lying on a plane, if appropriate a curved plane, And has a honeycomb structure. The honeycomb structure 3 composed of hollow cavities and the hollow cavities are made of non-metallic material impregnated with resin, while the covering layers 1, 2 glued to the hollow cavities are made of glass fibers impregnated with synthetic resin. figure 2 shows the basis of figure 1 The structure composed of the parts 1, 2, 3 after sticking together can be clearly seen that the covering layers 1, 2 are roughly parallel ...

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PUM

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Abstract

The invention relates to an aircraft side fairing, with a component (9) in the form of individual hollow chambers (12, 13, 14) which are arranged essentially in a preferably curved plane and are arranged between two cover layers (1, 2), wherein a gastight film which completely encases the component (9) with the hollow chambers (12, 13, 14) is provided and, after application of a vacuum to evacuate the hollow chambers (12, 13, 14), surrounds the component (9) with the hollow chambers in a gastight manner.

Description

technical field [0001] The invention relates to an aircraft side fairing with a core material in the form of a separate hollow cavity substantially arranged in a plane and sealed between two covering layers with insulation towards the outside of the aircraft layer and trim layer facing the cabin. Background technique [0002] Existing aircraft side fairings consist of a core material, which in particular is arranged approximately in a plane in the form of a separate hollow cavity and is sealed between two covering layers, with an insulating layer towards the outside of the aircraft And the trim layer facing the cabin. In this case, said core material consists of cavities, in particular a honeycomb hollow cavity structure of resin-impregnated non-metallic material. In the side fairing of the type described, the covering layers are arranged above and below the honeycomb structure and bonded thereto. The covering is made of fiberglass fabric impregnated with synthetic resin....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B3/12B64C1/12B64C1/40F16L59/065
CPCF16L59/065B64C1/40B32B3/12B32B3/26B64C1/066Y02T50/46Y10T428/231Y02T50/40
Inventor 赖纳·米勒格奥尔格·米泰勒
Owner AIRBUS OPERATIONS GMBH
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