Patent ID: 8889050

Claim:
A method for producing a fibre composite component for the aviation and aerospace industry, which comprises the following steps: forming a mould core by a compression moulding process using a core tool for establishing an outer shape of the mould core, wherein the mould core is formed from a cork-containing material as a solid profiled part or as a hollow core with a core inner space, wherein the cork-containing material consists of a cork powder mixed with a binder and filler or a compound of cork granules and rubber granules, wherein the cork containing material is introduced into the core tool and brought into the desired shape with the cross section of the mould core, and wherein the mould core is provided with at least one fixing element; arranging the mould core formed thus such that it rests against an at least part cured reinforcing element on a base component of the fibre composite component to be produced for forming at least one mould portion of the fibre composite component to be produced, and for fixing the mould core on the reinforcing element, the at least one fixing element of the mould core cooperates magnetically with at least one fixing aid element which is removably attached to the reinforcing element; and charging in multiple stages at least the mould portion with heat and/or pressure to produce the fibre composite component; wherein the mould core is at least partly provided with a reinforcing layer consisting of tear-proof woven fabric, and wherein the reinforcing layer forms a separating layer preventing the material of the mould core from adhering to the core tool during forming or the reinforcing element during charging.