A connection arrangement includes a first plastic component, a second plastic component, and a closed induction ring. The first plastic component has a first joining region designed as a receptacle, and at one end, the second plastic component has a second joining region introduced into the first joining region. At the joining regions, the induction ring is at least partially fused into the two plastic components such that at one contact region between a first plastic melt of the first plastic component and a second plastic melt of the second plastic melt, a material-conclusive connection is generated. In this case, the induction ring is melted into the first plastic component while forming at least one first undercut, and is melted into the second plastic component while forming at least one second undercut such that between the plastic components and the induction ring, one each form-fitting connection is created.

Systems and methods are provided for fabricating a hybrid composite part. A method includes braiding a first set of fibers to form a weave having a closed cross-sectional shape, braiding a second set of fibers into the weave that are chemically distinct from the first set of fibers, impregnating the weave with a resin, and hardening the resin within the weave to form a hybrid composite part.

Systems and methods are provided for fabricating a hybrid composite part. A method includes braiding a first set of fibers to form a weave having a closed cross-sectional shape, braiding a second set of fibers into the weave that are chemically distinct from the first set of fibers, impregnating the weave with a resin, and hardening the resin within the weave to form a hybrid composite part.

Integrated pultruded composite profiles such as rotor wings and blades for electric vertical take-off and landing aircraft, light helicopters, wind turbines, and other rotor wing applications and integrated design and processing methods for making same are disclosed. The present invention provides a plurality of web ribs for stiffening and supporting an outer skin which can comprise fabric plies, a metallic skin, or a thermoplastic composite skin. A process and method to continuously pultrude integrated composite airfoil profile with variable aerodynamic twist is also disclosed. Utilization of a stranded metallic wire rope that enables the leading edge weight to be continuously in-situ fed into the pultrusion process and effectively retained in the pultruded product is also disclosed. Utilization of fiber reinforcement impregnated with matrix resin that is loaded with high density powder for the leading edge weight is also disclosed.

A method of joining workpieces includes the steps of bringing a first workpiece and a second workpiece together, induction heating a susceptor material, and pressing the workpieces together. Each workpiece may include a thermoplastic material, and the workpieces are brought together at a joint interface so that a protrusion of the first workpiece is aligned with a receptacle of the second workpiece. The susceptor material is in contact with the thermoplastic material of the first workpiece during heating such that the thermoplastic material of the first workpiece softens. The step of pressing is performed while the thermoplastic material of the first workpiece is softened, thereby reshaping the first workpiece where the susceptor material is in contact with the thermoplastic material of the first workpiece. The protrusion is deformed to form an interlock with the receptacle at the joint interface.

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.

System includes a first object having an energy-assisted bonding (EAB) mechanism along a surface of the first object. The EAB mechanism includes a heat-activatable adhesive layer and a carbon-filled (CF) sheet material. The CF sheet material is electrically conductive for resistive heating. A control sub-system is configured to control a coupling actuator to drive an actuator body toward the first object, wherein the actuator body and the first object engage each other. The coupling actuator is configured to apply pressure to the EAB mechanism along the surface of the first object. The control sub-system is also configured to control the power source to apply a current through the CF sheet material of the EAB mechanism to provide thermal energy through resistive heating that activates the adhesive layer along the interface.

Disclosed herein are methods, devices, and systems for manufacturing wind turbine blades which in some instances require using new blade joint designs. The blade joint designs described herein may allow for contact in places where welds will be made, which allows for existing manufacturing tolerances to be used while still enabling the use of thermal welding for wind turbine blades.

An induction sealing device for heat sealing packaging material for producing sealed packages of pourable food products, said sealing device comprising: an inductor configured to induce a current in the packaging material, the inductor comprising conductor elements; a polymer insert holding said conductor elements; and a supporting body holding said polymer insert; wherein the polymer insert comprises a polymer matrix into which boron nitride particles are dispersed.

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.