Method for producing a core composite with double-sided surface layers

A technology for composite parts and covering layers, applied in the field of manufacturing core composite parts, can solve the problems of poor aerodynamic performance, reduced load capacity of mechanical structure, difficult winding and/or laying of covering layers, etc., and achieve the effect of aesthetic performance

Active Publication Date: 2011-04-06
AIRBUS OPERATIONS GMBH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, such a folded honeycomb core is only difficult to wind and/or lay down the covering layer, because in this case no at least section-by-section continuous curved surface is produced, but rather a polygonal character with several multi-parts surface geometry of
However, core composite parts with such discontinuous surface geom

Method used

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  • Method for producing a core composite with double-sided surface layers
  • Method for producing a core composite with double-sided surface layers
  • Method for producing a core composite with double-sided surface layers

Examples

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Embodiment Construction

[0039] figure 1 Shown is a core composite part with a sandwich structure produced according to the method according to the invention, which has curvatures in the spatial direction. The two covering layers covering both sides of the folded honeycomb core are only shown in outline, while the rest are shown transparent in order to expose the inner structure of the folded honeycomb core.

[0040] The core composite part 1 has an upper covering layer 2 and a lower covering layer 3 , between which a folded honeycomb core 4 is arranged. Both the covering layers 2, 3 and the folded honeycomb core 4 are curved in the spatial direction. In principle, this method can be used to produce flat, single- or double-bending (spherical) core composite parts with a very high load-bearing capacity. The folded honeycomb core 4 has a plurality of parallel, continuous and trapezoidal (drainage) channels 5 , 6 . The channels 5 , 6 are bounded by base lines 7 to 9 and apex lines 10 to 12 , which lik...

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PUM

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Abstract

The invention relates to a method for producing, planar, simple or doubly folded core composites (1, 23) with at least one folded honeycomb core (4, 19). A hardening and later removable core filler (15, 16) is introduced into the through drainage channels (5, 6) of the folded honeycomb core (4, 19) before application of the initially unhardened surface layers (2, 3, 13, 22) in order to prevent a penetration of the cover layers, (2, 3, 13, 22) into the channels (5, 6) of the folded honeycomb core on the application and/or hardening of the surface layers (2, 3, 13, 22) and to achieve surfaces of the core composite (1, 23) without edges or polygons.

Description

technical field [0001] The invention relates to a method for producing a core composite part having a folded honeycomb core with covering layers on both sides, wherein the folded honeycomb core has drainage channels running parallel to the covering layers. Background technique [0002] In the aircraft industry, the CFK-sandwich-nacelle is produced separately by the winding method. The core composite parts used for this purpose are constructed with a honeycomb core with small-volume cells in order to avoid depressions of the applied covering layer in the region of the honeycomb and thus to avoid restricted, in particular structural, aerodynamic and optical defects. [0003] Cell-shaped honeycomb cores of this type are not suitable for winding a one-piece fuselage section for modern large passenger aircraft. On the one hand, the honeycomb core used lacks drainage capacity. Condensation water penetrating into the core composite part and / or generated inside the core composite...

Claims

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Application Information

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IPC IPC(8): B32B3/12B32B3/28B32B38/10
CPCB29D99/0021B29K2063/00B32B38/10B29K2105/246B32B3/12B32B37/0007B29L2031/608B29C70/086B29K2707/04B32B37/146B32B5/024B32B5/026B32B5/26B32B7/14B32B15/14B32B29/02B32B2260/021B32B2260/028B32B2260/046B32B2262/101B32B2262/106B32B2307/50B32B2307/718B32B2605/18B32B7/05Y10T428/24157Y10T156/103Y10T156/1025Y10T156/1033Y10T156/1051Y10T428/24149
Inventor 迈克尔·科拉克斯沃尔夫-迪特里希·多尔辛斯基
Owner AIRBUS OPERATIONS GMBH
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