We disclose a component of an injection molding tool that includes a one piece side of a mold built up by additive manufacturing using a polymer, the side of the mold defining part of an injection cavity. The side of the mold further includes an injection port coupled to the injection cavity and a heating fluid manifold separated from the injection cavity by a heat transfer wall. The heat transfer wall is reinforced against pressure in the injection cavity by a backing of engineered supports. Inlet and outlet ports are coupled to the heating fluid manifold, configured to channel a thermally conductive fluid into and out of the heating fluid manifold. Additional additive manufacturing features and material properties are described. Complementary methods of manufacturing also are disclosed.

The present disclosure relates to a prepreg, a preparation method thereof and a fiber-reinforced composite material prepared therefrom. The preparation method of a prepreg may include an aramid fiber base material with improved wettability to resin, can increase a thickness reduction rate during molding of the prepreg, has an appropriate resin content, and can provide a prepreg suitable for molding by an out-of-autoclave process. In addition, the prepreg may provide a fiber-reinforced composite material that exhibits a thin thickness and a high resin content even by an out-of-autoclave process, and shows high strength and low moisture absorption

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 system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A thermally expandable composition includes at least one epoxy-functional polymer, at least one endothermic chemical blowing agent, at least one free radical initiator, and at least one guanidine derivative. The invention is also related to a baffle and/or a reinforcement element for hollow structures including the thermally expandable composition, to a process for manufacturing the baffle and/or the reinforcement element, to use of the baffle and/or the reinforcement element for sealing, baffling, or reinforcing of a cavity or a hollow structure, and to a method for sealing, baffling and/or reinforcing a cavity or hollow structure.

A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

The purpose of the present invention is to provide a sandwich structure that has both excellent heat dissipation properties and excellent mechanical properties. In order to achieve this purpose, the sandwich structure of the present invention has the following structure. The sandwich structure includes a core member (I), and a fiber reinforced member (II) disposed on both sides of the core member (I), wherein the core member (I) includes a sheet-shaped heat conductive member (III) having an in-plane thermal conductivity of 300 W/m.K or more.

An additive manufacturing apparatus includes an additive manufacturing print head and a nozzle that receives a bio-based shape memory polymer material and a bio-based material. The nozzle extrudes the bio-based shape memory polymer material and the bio-based material onto a substrate to form a bio-based shape memory polymer part or product.

A method for fabricating a composite wing structural component for an aircraft is described. The method comprises extruding a filler material into each mold channel of a plurality of mold channels of a die to form a plurality of filler segments, removing the plurality of filler segments from the plurality of mold channels of the die, and arranging the plurality of filler segments in a space in the composite structural component, the space being defined by a radius of the composite structural component, such that the filler segments are in end-to-end contact. The method further comprises curing the plurality of filler segments in the space to fuse the plurality of filler segments.

A method and system for determining the quality and configuration of a structure that is constructed from a thermoformable material, such as a thermoplastic or thermoset material, and in particular thermoplastic composite tapes, where heat is applied to cure the thermoformable material. The quality of the build is monitored during the construction of the structure by determining the differential heat flux in the material as it cools from its elevated temperature. The system and method also may determine the location of defects in a structure being constructed so that remedial measures may be taken or production operations halted to address the defect. A transient thermal effect is applied to the structure being monitored, such as the thermoformable material being applied, which may be implemented from the applied heating of the thermoformable construction application process or additional heating.