A system, apparatus, or method for joining components is provided. The system applies force along an axis, with a friction pin, to a first substrate, such as with a joiner or joining apparatus. The system also frictionally melts a portion of the first substrate adjacent the friction pin by rotating the friction pin about the axis at a first speed within the first substrate. The system also applies force to the second substrate along the axis and frictionally melts a portion of the second substrate adjacent the friction pin by rotating the friction pin at a second speed within the second substrate. The system embeds a portion of the friction pin within the first substrate and the second substrate. In some configurations, the first speed and the second speed are substantially equivalent. In other configurations, the first speed is different from the second speed.

A method for producing a fiber composite component assembly having at least first and second plate-shaped composite structures made from synthetic resin embedded fibers, the at least first and second fiber composite components having a plurality of partial regions not containing synthetic resin is described. The method includes positioning the at least first and second fiber composite components, the partial regions having been brought to flush conformity with each other, bonding the at least first and second positioned fiber composite components by the adhesive layer arranged in between, placing mechanical reinforcement means through the partial regions, infusing the dry partial regions with synthetic resin, and curing the synthetic resin placed in the partial regions.

A layered composite assembly may include a plurality of composite fiber layers stacked onto one another. Each of the plurality of composite fiber layers may include a main body including a plurality of composite fibers. The main body may be pre-impregnated with at least one resin. Each composite fiber layer also includes a plurality of layer-securing pins secured to the main body. The layer-securing pins are configured to mechanically connect the main body to an adjacent composite fiber layer.

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 of forming a composite preform containing multiple laminates is disclosed. The method may include providing a first sublaminate comprising stacked fibers woven into a fabric; providing a second sublaminate comprising stacked fibers woven into a fabric; joining the first sublaminate and the second sublaminate forming a component comprising a region of discontinuity sandwiched between the first sublaminate and the second sublaminate; rigidizing the component; and softening the region between the first sublaminate and the second sublaminate. In illustrative embodiments, the method may include manipulating the region of discontinuity between the first sublaminate and the second sublaminate to reduce the incoherence between the sublaminates by moving fibers from the sublaminates through at least part of the region between the first sublaminate and the second sublaminate.

A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.

A method of joining first and second layers of polymeric composite material includes disposing a portion of a molded insert having a bottom end into a top surface of a first layer of material and then applying a layer of adhesive between the top surface of the first layer and a bottom surface of a second layer of material to create a bond-line thickness. Next, a top surface of the second layer is pierced with a headless end of a fastener and interlocked into the molded insert. A layer of protective coating is then applied to the top surface of the second layer of material to cover the interlocked fastener.

A junction structure includes a first metallic material, a second material different in type from the first metallic material, and a welding wire as a third material similar to the first metallic material. The second material is stacked on the first material. The molten metal of the third metallic material is deposited by arc welding into the through part of the second material so as to form a flanged or tapered bead, so that the first and third metallic materials and the second material are fixed together.

The present disclosure relates to a fibre reinforced polymer (FRP) tube, the tube comprising a plurality of concentric layers of an FRP material forming a shell of the tube. At least one blind threaded longitudinal bolt hole is provided from a transverse end surface of the shell. The bolt hole extends in at least three of the plurality of layers, a middle layer encompassing a plane passing through a center of the bolt hole, an inner layer encompassing a plane of an innermost extent of the bolt hole, and an outer layer encompassing a plane of an outermost extent of the bolt hole. The fibre filament of each of the inner and outer layers has been wound at a first angle to the longitudinal axis and the fibre filament of the middle layer has been wound at a second angle to the longitudinal axis.

A roller coaster track may comprise a laminate and a metal bearing layer. A method of manufacturing a roller coaster track may comprise manufacturing a laminate, manufacturing a metal bearing layer, and assembling the laminate and bearing layer. The bearing layer may be at least partially filled with grout. A method of repairing a wood roller coaster track may comprise removing a layer of laminate, and replacing the layer with a metal bearing layer.