The present invention relates to a method for producing a folded core structure, particularly in the aerospace field, comprising the following steps: Initially a low-cross-linked, pre-impregnated semi-finished fibre component is provided. Subsequently heat is brought into predetermined regions of the pre-impregnated semi-finished fibre component, particularly using a laser, so as to highly cross-link the resin matrix in predetermined regions and so as to consequently generate a pattern of low-cross-linked and high-cross-linked regions in the semi-finished pre-impregnated fibre component. In a further step, of the method the pre-impregnated semi-finished fibre component is folded along the low-cross-linked regions that serve as hinges. Hereupon, the folded, pre-impregnated semi-finished fibre component is cured to the folded core structure. Compared to the known embossing method, in the method according to the invention an extensive tool for supporting the pre-impregnated semi-finished fibre component after the folding is advantageously omitted. Moreover, using the method according to the invention also tissue-like semi-finished fibre components can be processed to folded core structures.