Provided is an adhesive that can provide quick bonding between thermoplastic resins and excellent bond strength, a structure having adhesion provided by the adhesive, and an adhesion method using the adhesive. The adhesive bonds a first member (11) containing a thermoplastic resin or a carbon fiber reinforced thermoplastic resin and a second member (12) containing the thermoplastic resin or the carbon fiber reinforced thermoplastic resin. The adhesive includes a thermoplastic resin as a main component containing a metal nano material that absorbs electromagnetic waves and generates heat.

A method to prepare a composite laminate object containing an extrusion grade 7xxx Al substrate and a fiber-reinforced polypropylene layer adhesively laminated to the substrate; is provided. The process includes shaping and cutting an extruded 7xxx aluminum to a profile, assembling a layered arrangement of the 7xxx Al profile as substrate, an adhesive film and a fiber reinforced polypropylene preform, heating the layered arrangement to a temperature of 160-175 C. to melt the polypropylene and activate the adhesive film, applying pressure to at least a surface of the fiber reinforced polypropylene preform to mold the preform to the shape of the extruded 7xxxAl substrate and obtain a semi-finished laminate object, cooling the semi-finished laminate object to 90 C., optionally, cooling the semi-finished laminate object to room temperature for inventory storage; heat treating the semi-finished laminate object at 90 C. for 2 to 8 hours; and then heat treating the semi-finished laminate object at 130 C. to 150 C. for 8 to 16 hours; and cooling the heat treated object to obtain the composite laminate object.

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 method for joining a device to an object with the aid of a combination of ultrasonic vibration energy and induction heating, wherein the device includes a portion of a thermoplastic polymer and a susceptor additive wherein this portion is at least partly liquefied or plasticized through the ultrasonic vibration energy in combination with the induction heating and wherein the joining includes establishing a connection between the device and the object which connection is at least one of a positive fit connection, a weld, a press fit connection, and an adhesive connection. The induction heating is applied for rendering the device portion suitable for absorption of ultrasonic vibration energy than other device portions by raising its temperature above the glass transition temperature of the polymer. The ultrasonic vibration energy is used for liquefying or at least plasticizing the thermoplastic polymer of the named device portion.

A device for electromagnetic spot welding of moulded parts includes a pressurizing body, first displacing means configured for moving a pressurizing surface of the pressurizing body against the moulded parts or vice versa to join contact surfaces of the moulded parts to be fused by welding under pressure, an inductor provided in the pressurizing body and configured to generate an electromagnetic field in at least the contact surfaces of the moulded parts, and a mechanical fastener configured to be heated by the electromagnetic field generated by the inductor, or by other means. Second displacing means are configured for moving the mechanical fastener towards the moulded parts and drive the heated mechanical fastener into the joined moulded parts to a position further than the contact surfaces of the moulded parts. A method for electromagnetic welding of moulded parts using the device.

Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.

An apparatus and method of closing a wide variety of thermoplastic tubes, in particular with Shore hardnesses of around 50 (A) to above 100 (A), where the tubes having inside diameters of 1.6 mm to 35 mm and/or wall thicknesses of 0.8 to 4.8 mm. The method involves use of a tube heater having at least one heating element. The heating element has at least four heatable regions which are movable with respect to one another. The tube heater is configured to enclose, in the applied state, at least 75% of the circumference of the tube while bearing against the latter over its circumference at at least four points which are spaced apart from one another. One of the key advantages is that, prior to compression, the tube can already have been heated at a plurality of points on the tube.

A method for assembling by welding at least two components of composite material includes positioning at least one connection layer of fibers so as to be interposed between the contact surfaces of the two components and/or positioned in the region of at least one contact surface of the two components, each connection layer having unidirectional fibers which are oriented in a direction different from the directions of the fibers of at least the fiber layers of the two components close to the contact surfaces. An induced electrical current is generated in a direction approximately parallel with the direction of the fibers of each connection layer. This method enables heating to be concentrated in the region of the contact surfaces. An assembly is disclosed of at least two components of composite material by carrying out the method.

A method for fastening material webs, such as roofing sheets made of plastic on a surface with fastening points (head disks including a hot-melt adhesive layer) arranged thereon using a self-propelled fastening unit (20) comprising the following steps: (A) detecting a route marking by means of a first detector (22) on the fastening unit (20) and moving the fastening unit along the route marking; (B) detecting and calculating the position of a head disk (14) by means of a second detector (24); (C) approaching and remaining at an operating position during the subsequent fastening process; (D) positioning an induction heater (30) and heating up the head disk (14) for a period of time Th; (E) removing the induction heater (30) and pressing the material web against the head disk by a cooling device (32); (F) taking off the cooling device after a predetermined time Tk has passed; (G) continuing with (A), until an end of the route marking is reached.

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.