Structural internal reinforcement element for a fuselage, and procedure for the manufacture of said structural element

A method for the manufacture of an internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its location in the longitudinal direction of the fuselage and a transverse direction perpendicular to the longitudinal direction, comprising the following steps:

• providing a first male mould, with the shape of an external reinforcement element,
• providing a second male mould, with the shape of an internal reinforcement element, the internal reinforcement element being adapted to be placed internally to the external reinforcement element in a direction transverse to the structural element,
• providing resin-impregnated fibre,
• placing part of the resin-impregnated fibre on the first male mould,
• placing part of the resin-impregnated fibre on the second male mould,
• removing the first male mould, so that the resin-impregnated fibre takes the form of the external reinforcement element,
• removing the second male mould, so that the resin-impregnated fibre takes the form of the internal reinforcement element,
• placing the internal and external reinforcement elements in a mould, the internal reinforcement element located internally to the external reinforcement element in a direction transverse to the structural element, in such a way that a transverse hollow is defined between both reinforcement elements,
• filling the transverse hollow between the internal and external reinforcement elements with pre-impregnated composite material, forming an intermediate element, and
• performing the compression moulding of the assembly, to obtain the structural reinforcement element.