Disclosed is a method of resistance welding between composite articles. A conductive element is provided between faying surfaces, having a plurality of lower resistivity electrode portions spaced apart along the length of the contact area between the composite articles. The electrode portions can be used to spot weld across the electrode portions, and along a longitudinal portion of the conductive element between the electrode portions by application of an electrical current. Also disclosed are apparatus for use in the resistance welding methods and composite articles and structures and elements incorporating the conductive element.

An induction welding system includes a first gantry, a second gantry, and a support structure. The first gantry includes a first frame and a first plurality of trunks. The first plurality of trunks defines a first curved inner support surface of the first gantry. The first curved inner support surface has a first curvature geometry. The second gantry includes a second frame and a second plurality of trunks. The second plurality of trunks defines a second curved inner support surface of the second gantry. The second curved inner support surface has a second curvature geometry which is different than the first curvature geometry. The support structure includes at least one tooling member defining a curved outer support surface of the support structure. The support structure is longitudinally moveable relative to the first gantry and the second gantry.

A reinforcing component for a structure of an aircraft or spacecraft has a first component region for reinforcing at least one other element, and at least one second component region, which is permanently connected to the first component region. The reinforcing component is formed using a thermoplastic plastics material in each of the first component region and the second component region. In the first component region, the thermoplastic plastics material forms a matrix in which continuous reinforcing fibres are embedded. In the second component region, the reinforcing component comprises discontinuous reinforcing fibres or is free of reinforcing fibres.

A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.

At least one exemplary embodiment is directed to an earpiece having a balloon and a stent where the balloon is mounted on the stent and the stent incorporates two or more channels including at least an inflation channel and an acoustic channel. In some embodiments the stent is configured to pass audio signals through the acoustic channel where the acoustic channel is independent of the inflation channel of the balloon. Other embodiments are disclosed.

The present invention relates to a wind turbine blade and a method for its manufacture. A lower shell part and an upper shell part are provided, each shell part having a leading edge and a trailing edge. A first shear web and a second shear web for connecting an inner surface of the lower shell part with an inner surface of the upper shell part are provided. The first shear web and the second shear web are connected by a first distance member in a chordwise direction. The first distance member is arranged for accommodating a variable chordwise distance between said first shear web and said second shear web. The first shear web and the second shear web are placed in the lower shell part and the upper shell part is mounted.

A two different process continued performance type product assembly device may include a punching jig having a punch and configured to ascend and descend, a punching tool located on a lower portion of the punching jig and having a punching die that is located below the punch during a punching work, a fusion tool located on the lower portion of the punching jig and having a fusion horn that is located below the punch during a fusion work, and a tool exchange cylinder configured to push the punching die so that the fusion horn secedes from a position below the punch during the punching work and to pull the punching die so that the fusion horn comes into the position below the punch during the fusion work.

A method of making a wind turbine blade (10) having a shear web (20, 22) bonded between first and second half shells (16, 18) is described. The method involves providing a web locator (40) on an inner surface of a half shell. The web locator has a fixed portion (42) and a spring portion (44) extending from the fixed portion. The spring portion is moveable relative to the fixed portion between compressed and relaxed states.

The present subject matter relates to a method for manufacturing a vehicle interior trim part comprising a decor layer which forms a groove, as well as a decor element which is welded in the groove) of the decor layer, wherein the decor element is brought into the groove and is subsequently fixed in the groove by way of welding. According to the present subject matter, a welding head, e.g. an ultrasound sonotrode, is used for welding, and this comprises a contact side which is equipped with a plurality of projections which are arranged distanced to one another in a row and which taper to their contact surfaces, and wherein the welding head for producing the seam is pressed against a rear side of the decor layer in the region of the groove, in a manner such that the individual projections of the row of projections in a longitudinal directions of the groove come into contact with the rear side of the decor layer in a manner offset to one another, wherein the projections have a width which corresponds at least to 50% of a width of the decor element.

Described is a heating means for thermally connecting two objects each having a plastic material, wherein, during the connecting, a first inner object is surrounded at least partially by a second outer object, and the heating means surrounds the first inner object at least partially along a complete circumferential course around the first inner object, and is located between the first inner object and the second outer object. The heating means has a ribbon-type structure. The ribbon-type structure has an auxiliary heating material, which is inductively heatable, wherein the auxiliary heating material is spatially distributed or arranged along the circumferential course such that an electrical conductivity is interrupted at at least one position along the complete circumferential course around the first inner object. Further described are an arrangement and a system each having such a heating means as well as a method for thermally connecting two plastic objects.