A method for assembling two tubes (1, 2) made from thermoplastic materials, that involves welding by heating two applied rotational contact surfaces of two parts of two tubes (1, 2), respectively, arranged end to end or overlapping coaxially (XX′). The method involves induction heating of at least one conductive welding element (4), arranged at the interface (3) between the two contact surfaces, by generating a magnetic field at said conductive welding element or elements, such that the melting of the thermoplastic materials constituting said contact surfaces produces a continuous and sealed weld at said interface on at least one closed loop along the entire perimeter of said interface.

A method of creating a weld between a liner of a section of lined pipe and an electrofusion fitting. The fitting comprises at least one heating element, which is suitably disposed on or in an outer surface of the electrofusion fitting and is electrically isolated from an inner surface of the fitting. The method comprises locating an end of the electrofusion fitting within an end of the section of lined pipe, locating an induction coil within a bore of the electrofusion fitting in the vicinity of the at least one heating element, and supplying electrical power to the induction coil to energise the at least one heating element by electromagnetic induction.

A method of coupling polymeric components utilizing electromagnetic energy is disclosed. The method can include obtaining a first component having a first coupling portion, a second component having a second coupling portion, and a susceptor. The method can also include mating the first and second components such that the susceptor is proximate the first and second coupling portions. In addition, the method can include applying electromagnetic energy to the susceptor. The susceptor can convert the electromagnetic energy to heat, which can melt portions of the first and second coupling portions about the susceptor to couple the first and second components to one another upon solidification.

A composite sandwich panel includes a first composite part and a second composite part. A plurality of stiffeners extend between the first and second composite parts. A fiberglass composite perimeter edge closeout is positioned along one or more edges of the first and second composite parts. The fiberglass composite perimeter edge closeout controls a magnetic flux to bond the first and second composite parts to the plurality of stiffeners.

A connecting arrangement includes a first plastic component, a second plastic component, and a closed induction ring that is arranged between the first and second plastic components in a joining gap that is partially filled with molten plastic. The first plastic component has a first joining region that is configured as a stepped receiving opening with a first joining contour. The second plastic component has a second joining region that is configured as a stepped shoulder with a second joining contour. The second joining region is inserted into the first joining region to form the joining gap. The first and second joining contours are adapted to one another so as to center the first joining region, the second joining region, and the induction ring in the joining gap with respect to one another. A method in one embodiment includes welding the first and second plastic components of the connecting arrangement.

A system and method for bonding a first layer of material to a second layer of material includes a first electrically conductive plate, a second electrically conductive plate spaced apart from the first electrically conductive plate. The second electrically conductive plate is electrically grounded. A high frequency generator in electrical communication with the first electrically conductive plate supplies high frequency electrical signals to the first electrically conductive plate. An adhesive applied to one of the first and second layers of material has an electromagnetic susceptor material that when subjected to the electric field heats the adhesive to an adhesive curing temperature to bond the first layer of material to the second layer of material. A clamping mechanism applies pressure to one of the first and second layers of material to maintain contact between the first and second layers until an adhesive cure time has lapsed.

An induction cooking system includes a first container that receives first contents and a second container sized to fit within the first container. The second container is composed of a ferromagnetic material such that the second container is heated in response to received electromagnetic radiation. An exterior surface of the second container is in contact with the first contents of the first container, and an interior surface of the second container is in contact with second contents placed within the second container.

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 multilayer structure selected from a reservoir, a pipe or a tube, for transporting, distributing or storing hydrogen, including, from the inside to the outside, at least one sealing layer and at least one composite reinforcing layer, the innermost composite reinforcing layer being welded to the outermost adjacent sealing layer, the sealing layers including at least one semi-crystalline thermoplastic polymer, the Tm of which is less than 280° C., wherein the at least one thermoplastic polymer of each sealing layer may be the same or different, and at least one of the composite reinforcing layers being of a fibrous material in the form of continuous fibers impregnated with a composition of at least one thermoplastic polymer P2j, the thermoplastic polymer P2j having a Tg greater than the maximum temperature of use of said structure (Tu), with Tg≥Tu+20° C., Tu being greater than 50° C.