The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Jan. 06, 2015
Filed:
Feb. 20, 2009
Michael Kolax, Hamburg, DE;
Wolf-dietrich Dolzinski, Ganderkeese, DE;
Michael Kolax, Hamburg, DE;
Wolf-Dietrich Dolzinski, Ganderkeese, DE;
Airbus Operations GmbH, Hamburg, DE;
Abstract
The invention relates to a method for manufacturing a core composite () having a folded honeycomb core () provided on both sides with cover layers () wherein the folded honeycomb core () has a number of drainage-enabling channels (). First a core filler material () is introduced into the folded honeycomb core () at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers () which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core () and stitched to this along the base lines (to) and/or apex lines () at least in some sections by means of a sewing thread (). The infiltration of the overall structure with a curable plastics material is then carried out followed by hardening by applying pressure and/or temperature. The core filler material () can to complete the process be removed again completely from the folded honeycomb core () by being dissolved and washed out or by melting and flowing out. Delamination of the cover layers () from the folded honeycomb core () is prevented by the stitching so that core composites () manufactured by the method according to the invention can be used in the primary structure of aircraft. The invention further relates to a core composite () manufactured according to the provisions of the method.