Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.

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.

A method for forming a fiber-reinforced thermoplastic hollow structure may comprise: abutting a first surface of a first flange of a shell and a second surface of a second flange of the shell with a mating component; disposing an end block laterally adjacent to the shell; applying a first load to a sidewall of the shell; applying a second load to the second flange of the shell; and vibrating one of the shell or the mating component while keeping a non-vibrating component stationary, the non-vibrating component including one of the shell or the mating component.

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 web packaging machine for forming a food product package from a lower web of packaging material and an upper web of packaging material includes a frame, a web transport conveyor extending along the frame and configured to transport the lower web of packaging material along the frame, and a die box pivotally coupled to the frame and configured to form or close the food product package. A lift assembly is pivotally coupled to the frame and configured to assist manual pivoting of the die box relative to the frame.

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.

A fuel system component used to supply a fuel to a fuel tank or used to discharge the fuel from the fuel tank comprises a first resin layer; and a second resin layer formed in a similar color to that of the first resin layer and configured to include a welding portion that is welded to the first resin layer and an exposed portion that is not adjacent to or in contact with the first resin layer. A belt-like portion is formed on a first resin layer-side surface of the exposed portion to be parallel to a boundary between the welding portion and the exposed portion and is configured to include at least one of a concave and a convex extended intermittently or continuously.

An apparatus (1) for processing cups (2), adapted to be filled with coffee or other products, whether solid or liquid, and to be closed with respective lids to form corresponding capsules, comprises: a plurality of pockets (50) for housing the cups (2); an infeed station (4) for receiving the cups (2) and placing them in respective pockets (50) of the plurality of pockets (50); at least one tool (31) for applying a process to a rear face (23B) of an annular flange (23) of a cup (2) housed a respective pocket (50), to form a sealing profile (230); an outfeed station (6) configured to release the cups (2) with the sealing profile (230) formed on them.

A method for creating a termination by attaching some kind of fitting to the end of a tensile member such as a cable. The end fitting is provided with an internal cavity. The cavity has a proximal portion that is adjacent to the area where the tensile member exits the fitting and a distal portion on its opposite end. A length of the tensile member's filaments is placed within this expanding cavity and infused with liquid potting compound. The method exploits the characteristic of a liquid potting compound as it transitions to a solid. The potting compound in one portion of the cavity is typically transitioned to a solid at a more rapid rate than other portions. Once the potting compound in one portion of the cavity has transitioned sufficiently to hold the filaments at the desired level, tension is placed on the tensile member and a small linear displacement may be imposed on the tensile member. This linear displacement tends to pull the filaments residing in the potting compound into better alignment and improve load sharing.