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

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...

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.

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