Skin-bonded threaded inserts may be installed within a sandwich panel by curing the insert in place as the sandwich panel is cured. Skin-bonded threaded inserts may include a collar that is transitioned between a raised position and a compressed position during installation of the skin-bonded threaded insert in the sandwich panel, due to compression of the sandwich panel during curing. Skin-bonded threaded inserts may include one or more flanges that engage one or more skins of the sandwich panel. Such flanges may be positioned between two skins, or between the core and a skin of the sandwich panel to secure the sandwich panel in place within the sandwich panel. Skin-bonded threaded inserts may be positioned within a sandwich panel without the use of potting compound and may engage with the skins of the sandwich panel, rather than relying on adherence to the core for sufficient pull-out and shear strength.

System and method for in-process cure monitoring of a material utilizes one or more sensors such as fiber Bragg gratings (FBGs) or phase-shifted FBGs (PS-FBGs) and at least one optical line fiber connected to the sensor(s). The sensor(s) and the optical line may be embedded in the material prior to curing the material may comprise a fiber reinforced polymer. Waves are excited into the material during curing thereof to form guided waves that propagate through the material. At least one wave metric of the guided waves is measured utilizing the sensor(s).

Provided are a novel filament for a three-dimensional printer, a winding, a method for producing a filament for a three-dimensional printer, and a method for producing a formed article. The filament for a three-dimensional printer includes a continuous reinforcing fiber impregnated with a thermosetting resin composition containing a thermosetting resin, the filament having a characteristic of being solid at 25° C.

The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.

A device for shaping at least one fibrous preform for producing a bladed part of a turbomachine, this device including a mould formed by several parts that are interlocked with each other, this mould defining at least one internal cavity configured to receive the preform and to enclose the preform integrally, this cavity being intended to have two platform areas and a blade area extending between the two platform areas, wherein the mould includes at least a lower shell, an upper shell, a side shell, and end shells, and in that each of the side and end shells includes three elements, respectively lower, intermediate and upper.

Provided is a method for manufacturing a fiber reinforced resin molded article capable of preventing oxidation and degradation of a liner making up a preform at a high temperature, and such a manufacturing device thereof. Prior to pouring resin into a mold, the method fills inert gas (nitrogen gas, for example) into the mold. After filling inert gas (nitrogen gas, for example) into the mold, the method closes an upper mold (second mold) placed with a gap (second gap) with a preform (i.e., brings it closer to the preform).

Systems and methods for forming insulation on magnet wire are provided. An extruder that includes one or more rotating screws may receive a thermoset polymeric material and process the thermoset polymeric material to increase its pressure and temperature. An extrusion crosshead assembly in fluid communication with the extruder may receive the thermoset polymeric material and press extrude the thermoset polymeric material as insulation onto a magnet wire. A curing device may then cure the extruded insulation material.

A structural reinforcement for an article including a carrier that includes: (i) a mass of polymeric material having an outer surface; and (ii) at least one consolidated fibrous insert (14) having an outer surface and including at least one elongated fiber arrangement having a plurality of ordered fibers arranged in a predetermined manner. The fibrous insert is envisioned to adjoin the mass of the polymeric material in a predetermined location for carrying a predetermined load that is subjected upon the predetermined location (thereby effectively providing localized reinforcement to that predetermined location). The fibrous insert and the mass of polymeric material are of compatible materials, structures or both, for allowing the fibrous insert to be at least partially joined to the mass of the polymeric material. Disposed upon at least a portion of the carrier may be a mass of activatable material.

A piston for a heavy duty diesel engine including a composite layer forming at least a portion of a combustion surface is provided. The composite layer has a thickness greater than 500 microns and includes a mixture of components typically used to form brake pads, such as a thermoset resin, an insulating component, strengthening fibers, and an impact toughening additive. According to one example, the thermoset resin is a phenolic resin, the insulating component is a ceramic, the strengthening fibers are graphite, and the impact toughening additive is an aramid pulp of fibrillated chopped synthetic fibers. The composite layer also has a thermal conductivity of 0.8 to 5 W/m.Math.K. The body portion of the piston can include an undercut scroll thread to improve mechanical locking of the composite layer. The piston can also include a ceramic insert between the body portion and the composite layer.

Provided is a useful improvement in a manufacturing method of a CF-SMC using a partially split continuous carbon fiber bundle. The manufacturing method of an SMC of the present invention includes (i) a step of drawing out a continuous carbon fiber bundle (10) from a package, the continuous carbon fiber bundle (10) having a filament number of NK and partially split into n sub-bundles in advance, (ii) a step of chopping the continuous carbon fiber bundle (10) drawn out from the package with a rotary cutter (234) into chopped carbon fiber bundles (20), and (iii) a step of depositing the chopped carbon fiber bundles (20) on a carrier film (41) traveling below the rotary cutter (234) to form a carbon fiber mat (30). In the manufacturing method, due to a fragmentation processing, in which at least some of the chopped carbon fiber bundles before being deposited on the carrier film (41) are fragmented by being brought into contact with a rotating body, a distribution of the filament number of the chopped carbon fiber bundles in the carbon fiber mat (30) is made different from that when the fragmentation processing is not performed.