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

Abstract

The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and / or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical properties, an ideal surface quality from the aerodynamic and aesthetic point of view, whereby a direct reprocessing of the core composites 1, 23 is possible without the need for further time and cost-intensive as well as in some circumstances weight-increasing finishing steps. With the method it is possible to manufacture in particular one-piece fuselage sections with wound core composites 1, 23 with a folded honeycomb 4, 19 as well as shell segments with laid cover layers 2, 3, 13, 22 for longitudinally divided (segmented) fuselage sections for large aircraft.

Description

Technical field [0001] The present invention relates to a method for manufacturing a core composite part having a folded honeycomb core with covering layers on both sides, wherein the folded honeycomb core has drainage channels extending parallel to the covering layer. Background technique [0002] In the aircraft industry, the CFK-sandwich-nacelle is manufactured separately by the winding method. The core composite part used for this purpose is constructed with a honeycomb core with small cells in order to avoid the coated cover layer from sinking in the area of ​​the honeycomb and thereby avoid restrictive, especially structural, aerodynamic And optical defects. [0003] Such a cell-shaped honeycomb core is not suitable for winding an integral fuselage section for modern large passenger aircraft. On the one hand, the honeycomb core used lacks drainage capacity. As a result, the condensed water that penetrates into the core composite component and / or is generated inside the cor...

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 geometries cannot be used for the skinning of fuselage sections of aircraft for various reasons

Because of the edged surfaces, in particular the aerodynamic properties of the components produced with the core composite component are reduced and also result in a significantly reduced mechanical structural loadability compared to a flat structure.

Images