Method and moulding core for producing a fibre composite...

B - Operations – Transporting – 29 – C

Patent

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Details

B29C 70/44 (2006.01) B29C 33/50 (2006.01) B29D 24/00 (2006.01)

Patent

CA 2651495

The invention relates to a method and amoulding core for producing a fibre composite component (22), in particular for aerospace, comprising the following method steps: introducing an elastic core sleeve (1) into a prestressing mechanism (3); expanding the core sleeve (1) that is introduced, for elastic prestressing of the same, by activating the prestressing mechanism (3); introducing a core body (13) through an opening (4) of the expanded core sleeve (1); releasing the core sleeve (1) by deactivating the prestressing mechanism (3), for the snug enclosing of the core body (13) by the core sleeve (1) and thus for the forming of the moulding core (14); and at least partly laying at least one semifinished fibre product (16) on the moulding core (14) that is formed, for the shaping of the fibre composite component (22) to be produced.

L'invention se rapporte à un procédé et à un noyau de moulage permettant de produire un composant composite à fibre (22), en particulier pour le domaine aérospatial, comprenant les étapes de procédé suivantes : introduction d'une chemise centrale élastique (1) dans un mécanisme de précontrainte (3) ; expansion de la chemise centrale (1) qui est introduite, pour une précontrainte élastique de cette dernière, en activant le mécanisme de précontrainte (3) ; introduction d'un corps central (13) à travers une ouverture (4) de la chemise centrale expansée (1) ; libération de la chemise centrale (1) en désactivant le mécanisme de précontrainte (3), pour l'enveloppement serré du corps central (13) par la chemise centrale (1) et de la sorte pour la formation du noyau de moulage (14) ; et la disposition au moins partielle d'au moins un produit semi-fini à fibre (16) sur le noyau de moulage (14) qui est formé, pour la mise en forme du composant composite à fibre (22) devant être produit.

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