Method for manufacturing a fibre composite component, fibre composite component, and structural component for an aircraft or spacecraft

The invention relates to a method for manufacturing a fibre composite component comprising a skin portion and a backing structure. Initially, a single-piece foam body or the parts of a multi-part foam body, which comprises at least one recess which is open towards a first side of the foam body, are prepared and positioned. Prior to, during or after the positioning of the foam body or the parts thereof, a rigidifying element for the backing structure or a preform or first semi-finished product for forming the rigidifying element is arranged in the recess at least in portions. A skin portion or a second semi-finished product for forming the skin portion is provided, and brought into contact, in regions, with the foam body on the first side thereof and with the rigidifying element or preform or first semi-finished product, causing the skin portion or second semi-finished product to be placed against the foam body at least in portions and the rigidifying element or preform or first semi-finished product to be positioned relative to the skin portion or second semi-finished product. The skin portion or second semi-finished product and the rigidifying element or preform or first semi-finished product in contact therewith are processed further in such a way that a fibre composite component is obtained in which the skin portion and the rigidifying element are interconnected. The invention additionally relates to a fibre composite component and to a structural component for an aircraft or spacecraft.