B - Operations – Transporting – 32 – B
Patent
B - Operations, Transporting
32
B
B32B 3/12 (2006.01) B32B 3/28 (2006.01) B32B 7/08 (2006.01) B32B 38/10 (2006.01)
Patent
CA 2719303
The invention relates to a method for manufacturing a core composite (1, 20, 26) having a folded honeycomb core (2, 21, 29) provided on both sides with cover layers (3, 4, 22, 23, 27, 28) wherein the folded honeycomb core (2, 21, 29) has a number of drainage- enabling channels (5). First a core filler material (16, 17) is introduced into the folded honeycomb core (2, 21, 29) at least in some areas in order to provide the filler material with sufficient stability for the subsequent sewing process. The cover layers (3, 4, 22, 23, 27, 28) which are not yet impregnated with a curable plastics material are then placed on the folded honeycomb core (2, 21, 29) and stitched to this along the base lines (6 to 8) and/or apex lines (9, 10) at least in some sections by means of a sewing thread (19). 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 (16, 17) can to complete the process be removed again completely from the folded honeycomb core (2, 21, 29) by being dissolved and washed out or by melting and flowing out. Delamination of the cover layers (3, 4, 22, 23, 27, 28) from the folded honeycomb core (2, 21, 29) is prevented by the stitching so that core composites (1, 20, 26) 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 (1, 20, 26) manufactured according to the provisions of the method.
L'invention concerne un procédé de fabrication d'une structure sandwich (1, 20, 26) comprenant un noyau alvéolaire plissé (2, 21, 29) pourvu de couches de recouvrement (3, 4, 22, 23, 27, 28) sur les deux côtés, ce noyau présentant des canaux (5) qui s'étendent parallèlement aux couches de recouvrement (3, 4, 22, 23, 27, 28) et peuvent être drainés. Selon ce procédé, une matière de remplissage de noyau (16, 17) est introduite au moins dans des régions du noyau alvéolaire plissé (2, 21, 29) pour conférer à ce dernier une stabilité suffisante lors du processus de couture ultérieur, puis les couches de recouvrement (3, 4, 22, 23, 27, 28) non encore imprégnées d'une matière plastique durcissable sont placées sur le noyau alvéolaire plissé (2, 21, 29) et cousues à celui-ci au moins par endroits le long de lignes de base (6 à 8) et/ou de lignes de sommet (9, 10) au moyen d'un fil à coudre (19). Une infiltration de matière plastique durcissable est ensuite réalisée dans l'ensemble de la structure et cette matière est durcie sous l'action de la pression et/ou de la température. La dernière étape du procédé consiste à retirer totalement la matière de remplissage de noyau (16, 17) du noyau alvéolaire plissé (2, 21, 29) par dissolution et rinçage ou par extraction par fusion.
Dolzinski Wolf-Dietrich
Kolax Michael
Airbus Operations Gmbh
Kirby Eades Gale Baker
LandOfFree
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