Abstract: An implant for electric resistance welding of elements made of composites, with a frame of thermoplastic materials, reinforced with conductive fibres, in a flat multilayered structure with an upper and lower surface, and includes an electrically resistant layer of a flat sheet with openings, made of a conductive material, additional layers made of the frame material, one of which covers the electrically resistant layer from the top, and the other one from the bottom. The implant includes porous insulating layers made of an electrically nonconductive material, one covers the implant from the top, contacting the upper layer of the frame material, and the other covers the implant from the bottom, contacting the lower layer of the frame material. The layers are merged with each other in a flat, multilayered inset placed between the welded elements, and the electrically resistant layer has electrical connections for connecting a source of electrical current.

Abstract: The disclosed embodiments relate to a method for repairing a damage to a thermoplastic composite element, in particular an aircraft component, wherein a socket is milled at the site of damage to the thermoplastic composite element. Then, in the socket a patch is formed from a thermosetting material containing a reinforcing phase of fabric layers and a matrix of thermosetting resin, the patch having a shape and size corresponding to the socket geometry. In the next step, the patch is cured, and finally the cured patch is glued into the socket by means of an adhesive.