A method of dissipating heat from a surface of a first thermoplastic composite (TPC) being inductively welded with a second thermoplastic composite (TPC) includes flexing a heat sink during placement to conform to the surface of the first TPC, cooling the heat sink, applying inductive heat to a weld interface area between the first TPC and the second TPC, and drawing off heat via the heat sink from the surface of the first TPC.

An end effector for welding composite components includes an end effector housing and a welding member mounted to the end effector housing. The end effector further includes a leading roller mounted to the end effector housing forward of the welding member and at least one follower roller mounted to the end effector housing aft of the welding member. The end effector further includes at least one first cooling air jet positioned to direct a first stream of cooling air toward the at least one follower roller.

A fiber-reinforced composite laminate for use in electromagnetic welding of molded parts of said laminates. The laminate has a plurality of structural layers, each formed of electrically conductive fibers embedded in a thermoplastic matrix. Eddy currents may be induced in the electrically conductive fibers by an electrical conductor that generates an electromagnetic field. The structural layers include a first, a second and, optionally, a third pair of two adjacently positioned structural layers. The first pair has an intermediate layer which allows eddy currents to flow between the two structural layers of the first pair. The second pair has an intermediate layer which prevents eddy currents from flowing between the two structural layers of the second pair. The optional third pair does not have an intermediate layer. The laminate shows efficient heating by an electromagnetic field.

A method of induction welding a first thermoplastic composite (TPC) to a second thermoplastic composite (TPC) includes inductively heating a weld interface area between the first TPC and the second TPC, and cooling a surface of the first TPC opposite the weld interface area while inductively heating the weld interface area.

A heat sink for use in induction welding includes a number of tiles, where the tiles are electrically non-conductive and thermally conductive, a joint flexibly joining the tiles together, and a fluid path formed through the heat sink for communicating a coolant therethrough.

A heat sink for use in induction welding includes a flexible backing and a number of tiles disposed on the flexible backing in a single layer, wherein the tiles are electrically non-conductive and thermally conductive.

A method of induction welding a first carbon fiber thermoplastic composite (TPC) to a second carbon fiber thermoplastic composite (TPC) using an induction coil includes aligning the first TPC with the second TPC to form a weld interface area, flexing a heat sink onto a surface of the first TPC between the weld interface area and the induction coil, and inductively heating the weld interface area with the induction coil.

A system for controlled induction welding of at least one weld seam area (A) of at least two surfaces of at least one workpiece is provided. The system comprises an inductor configured to be arranged in conjunction with the at least one workpiece, a processing means configured to generate an electromagnetic field by applying an alternating voltage to the inductor so as to inductively heat at least one of the surfaces so that the weld seam area (A) is welded together, simultaneously measure at least one parameter (P) of the at least one workpiece at least based on the generated electromagnetic field, detect a change of the at least one parameter (P), and determine a temperature estimation of the at least one workpiece based on said detected change.

A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.

A joint between dissimilar thermoplastic materials comprising a first thermoplastic material layer; a second thermoplastic material layer having a melting point temperature different from a melting point temperature of the first thermoplastic material layer; and an interface layer coupled between the first thermoplastic material layer and the second thermoplastic material layer; wherein the interface layer is configured to join the first thermoplastic material layer and the second thermoplastic material layer together to form the joint, wherein the interface layer comprises a melting point temperature having a value selected from the group consisting of between the melting point temperature of the first thermoplastic material layer and the melting point temperature of the second thermoplastic material layer; or lower than the melting point temperature of the first thermoplastic material layer and the melting point temperature of the second thermoplastic material layer.