Abstract: A method for integrating metallic components into composite materials comprising curing layers of dry composite fibres (2) in a tool (3) in conjunction with at least one metallic element (1), which is the metallic element (1) that is placed for the curing process in the exact position in which a final part (5) is intended to be placed, and the layers of dry composite fibres (2) are placed around the metallic element (1) and the final part (5) is obtained with at least one metallic element (1) completely integrated into a composite material (6). The method is preferably used to integrate a bushing into a composite material. The bushing to be used can have a special surface, depending on the loads that the final parts must bear.

Abstract: The present invention relates to a process for manufacturing composite structures formed by two subcomponents of the same material, characterized in that it comprises the following steps: providing a first subcomponent (13), particularly a skin; providing a tool (15) made of a composite and precured for the manufacture of the second subcomponent (17), particularly a stiffener; positioning said tool (15) on said first subcomponent (13); applying preimpregnated composite (21) on said tool (15) so as to form the second subcomponent (17); consolidating the composite structure by means of a process of curing the assembly resulting from the previous steps under suitable pressure and/or temperature conditions.

Abstract: The present invention relates to a process for manufacturing composite structures formed by two subcomponents of the same material, characterized in that it comprises the following steps: providing a first subcomponent (13), particularly a skin; providing a tool (15) made of a composite and precured for the manufacture of the second subcomponent (17), particularly a stiffener; positioning said tool (15) on said first subcomponent (13); applying preimpregnated composite (21) on said tool (15) so as to form the second subcomponent (17); consolidating the composite structure by means of a process of curing the assembly resulting from the previous steps under suitable pressure and/or temperature conditions.