A method is for manufacturing a honeycomb structure including a core material in which a hole is formed to penetrate in a thickness direction and is arranged in a plane direction, and a skin material that is stacked on a surface of the core material. The skin material includes a thermosetting resin. The method includes half-curing the thermosetting resin by placing the skin material in a bag and heating the skin material in a state where an inside of the bag is evacuated and an outside of the bag is under an atmospheric pressure; stacking the skin material in which the thermosetting resin is half-cured onto a side of the surface of the core material; and bonding and integrating the core material and the skin material with each other by pressurizing and heating the stacked core material and skin material with the use of a sealing pressurizing heating facility.

A wind turbine blade comprising first and second adjacent blade sections arranged end to end along the length of the blade. Each section comprises an aerodynamic fairing and a spar. Each spar comprises a shear web extending across the fairing and a pair of spar caps, one at either end of the shear web. Each spar cap in the first section has a different cross-sectional shape and/or material from the respective spar cap in the second section and wherein the spar cap in the first section is joined to the respective spar cap in the second section via a connection piece. Each connection piece is a pre-cured component extending along the length of the blade from a first inclined end configured to connect to a first complimentary inclined end of a spar cap of the first blade section and a second inclined end.

A method for producing a shaped article includes a second web forming step, in which a mixture containing fibers and a binding material is deposited in the air, the binding material containing starch and an alkali metal salt; a moistening step, in which the mixture is supplied with water; and a sheet-forming step, in which heat and pressure are applied to the mixture supplied with water to give a sheet. The alkali metal salt content of the binding material is 2.0% by mass or less of the total mass of the starch.

A scrap collection assembly for a tape lamination head that applies a plurality of composite tape segments includes a crack-off assembly with a scrap crack-off redirect roller configured to engage one or more composite tape segments and one or more scrap portions; a secondary crack-off roller configured to engage one or more composite tape segments and one or more scrap portions; a pivot that connects the crack-off assembly to the tape lamination head, wherein the secondary crack-off roller selectively moves about the pivot to change a direction of composite tape movement; and a conveyor that receives the scrap portion(s) from the secondary crack-off roller.

Invasive medical devices including a substantially non-eluting antimicrobial treatment are disclosed. One or more external and/or internal surfaces of the medical device include a substantially non-eluting copper-coated surface that assists in preventing microbial colonization of the coated surface. This in turn reduces the incidence of infection to the patient originating from the medical device. In one embodiment, a catheter assembly is disclosed and comprises an elongate catheter tube that defines at least one lumen, at least one extension leg including a luer connector, and a bifurcation hub including at least one fluid passageway that provides fluid communication between the extension leg and the lumen. A substantially non-eluting copper coating is disposed on a surface of at least one of the lumen, the extension leg, the luer connector, and the fluid passageway. The coating is applied via an electroless deposition process. A water-shed coating is disposed on the copper coating.

A method for manufacturing an outer skin of a rotor blade includes forming an outer skin layer of the outer skin from a first combination of at least one of one or more resins or fiber materials. The method also includes forming an inner skin layer of the outer skin from a second combination of at least one of one or more resins or fiber materials. More specifically, the first and second combinations are different. Further, the method includes arranging the outer and inner skin layers together in a stacked configuration. In addition, the method includes joining the outer and inner skin layers together to form the outer skin.

A method of manufacturing is presented. The method includes providing a plurality of structural layers comprising a plurality of composite rods, wherein at least one structural layer from the plurality of structural layers is attached to a separation layer. The method further includes stacking the plurality of structural layers, detaching the separation layer from the at least one structural layer, and curing the plurality of structural layers to form a structural component of a wind turbine blade.

A method for making a composite-metal hybrid shaft for a rotorcraft includes providing a tubular metal member that has an internal surface defining a space therein, preparing a composite member using a curing tool, curing the composite member, creating a cured composite member, expanding the metal member with heat, placing the cured composite member into the space defined by the internal surface of the expanded metal member, and allowing the expanded metal member to cool.

A method of sealing an aircraft wing vent stringer may include placing a movable sealant sled in a vent stringer cavity of an aircraft wing. The sealant sled may include a sealant source configured to apply sealant to a wing portion within the vent stringer. The sealant sled may be transported through the cavity in a longitudinal direction defined by the wing, thereby applying a layer of sealant to the wing. In some cases, vent stringer may be abraded and/or washed before sealing. In some cases, two or more layers of sealant may be applied, one of which may be a secondary fuel barrier.

A system (100) for making a prepreg composite sheet (300) comprising contoured charges (308) comprises first means (102) for forming precursor outline regions (206) in a resin film layer (200). The system (100) also comprises second means (106) for impregnating a fiber reinforcement (220), comprising fibers (222), with the resin film layer (200), comprising the precursor outline regions (206), to form the prepreg composite sheet (300). The prepreg composite sheet (300), as so formed, comprises non-impregnated outline regions (310) that define the contoured charges (308). The non-impregnated outline regions (310) in the prepreg composite sheet (300) correspond to the precursor outline regions (206) in the resin film layer (200). The system (100) further comprises third means (104) for guiding the fiber reinforcement (220) and the resin film layer (200) to the second means (106). The resin film layer (200) comprises the precursor outline regions (206) formed by first means (102).