A control rod for incorporation into a composite assembly with at least a first composite preform, a second composite preform, and a cured resin includes a shaft defining an axis, wherein the shaft is disposable within an aperture in the composite assembly, and a plurality of threads disposed on at least a portion of the shaft. The shaft is made from, among other materials, a thermoplastic material. The threads define a thread pitch that encompasses more than one individual fiber layer forming at least one of the first composite layer and the second composite layer.

A method for producing insulating profiles comprises manufacturing a profile body and a first functional element separately, and the profile body and the first functional element are supplied to an ultrasonic welding device, wherein the profile body and the functional element are connected to one another by a material bond by formation of a welded joint. The profile body and the functional element are brought together into a predetermined first cross-sectional geometry during formation of the welded joint and are thereafter guided in this cross-sectional geometry until the plastics material of the welded joint solidifies to such an extent that the profile body and the first functional element are fixed in the predetermined cross-sectional geometry.

A resin frame includes frame members combined into a frame shape that includes a corner portion, and a joint portion joining a pair of the frame members which are adjacent to each other at the corner portion. The joint portion includes an entire-surface welded portion, in which end surfaces of the pair of the frame members are welded to each other over an entire surface in a thickness direction of a plate portion of the frame members, and a partial welded portion, in which the end surfaces of the pair of the frame members are welded to each other on one side of the entire surface in the thickness direction while another side of the entire surface in the thickness direction is not welded. The entire-surface welded portion and the partial welded portion are present at different portions on an outer periphery of the joint portion.

A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.

Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

A composite article including a plurality of layers each comprising bundles of fibers separated by spaces; pins bonded to a side of at least one of bundles and extending or built through the spaces between the layers; and a resin combined with the layers and the pin. The pins form a physical barrier preventing or reducing propagation of cracks in an x-y plane of the composite article.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

The machine (1) comprises at least one main welding device (3) of a first profiled element (4) and a second profiled element (5) which extend along their respective longitudinal directions and are each provided with at least one extremal area to be welded (6), the main welding device (3) comprising: main retaining means (18, 19) of the profiled elements (4, 5); main heating means (20) adapted to heat the extremal areas to be welded (6); main displacement means (21) of the main retaining means (18, 19) adapted to displace the profiled elements (4, 5) between a mutual spacing away position and a mutual approaching position;
wherein the main heating means (20) comprise two heating plates (27), each of which can be placed in contact with a respective extremal area to be welded (6) and arranged substantially parallel to each other at a predefined distance to define a free volume (V) positioned between them.

Fiber-reinforced thermoplastic composite structural members (FRTCSM), aircraft including the same, and related methods are disclosed herein. The FRTCSMs include a first thermoplastic sub-structure that includes a first web, a first flange that extends away from the first web, and a first transition region between the first flange and the first web. The FRTCSMs also include a second thermoplastic sub-structure that includes a second web, a second flange that extends away from the second web, and a second transition region between the second flange and the second web. The first web is welded to the second web. The aircraft include at least one FRTCSM. The methods include positioning the first thermoplastic sub-structure and the second thermoplastic sub-structure such that the first web faces the second web, compressing the first web and the second web together, and welding the first web and the second web to one another.

A rotary wing aircraft that comprises a structural arrangement with at least one first fiber reinforced polymer component and at least one second fiber reinforced polymer component that are spaced apart from each other by an interspace and that are rigidly attached to an associated structural component, wherein the at least one first fiber reinforced polymer component and the at least one second fiber reinforced polymer component are at least partly interconnected by means of an electrically conductive connection, and wherein the electrically conductive connection comprises at least one sprayed layer of electrically conductive particles, the at least one sprayed layer of electrically conductive particles being provided in the interspace.