Methods for placing an indicia on a composite structure generally include printing the indicia on a first film surface of a coating film, with the coating film being in a partially cured state at the time the printing the indicia is performed, and positioning the coating film on a partially cured composite structure such that a second film surface of the coating film faces and is positioned against a surface of the composite structure, with the second film surface being opposite the first film surface. Finally, the coating film and the composite structure may then be co-cured. Systems for printing an indicia on a composite structure generally include the coating film, a printer configured to print the indicia on the first film surface of the coating film, a securement configured to secure the coating film during printing, and a curing device for co-curing the coating film and the composite structure.

Prepregs having a UV curable resin layer located adjacent to a first thermally curable resin layer or sandwiched between first and second thermally curable resin layers wherein the UV curable resin layer is uncured or partially cured as well as methods for preparing laminates using the prepregs wherein the laminate includes at least one UV curable resin encapsulated electrical component.

A self-healing vacuum insulation panel and a method of manufacture are provided. The vacuum insulation panel includes a self-healing, multi-layer barrier film including a separator between a curing agent and a curable resin. Upon damage to the separator, the curing agent penetrates the separator due to a pressure differential across the barrier film and reacts with the curable resin to seal any cuts or punctures. The curing agent and the curable resin can be selected to have long term stability and a short reaction time with no need for external stimuli. As a result, the multi-layer barrier film can retain the internal vacuum and maintain a desirably low thermal conductivity using low-cost, commercially available epoxies and curing agents.

A method is provided for managing the temperature of heat sensitive material located near a repair patch being thermally cured on a composite skin using a heating blanket. The method comprises configuring an assembly of thermally conductive cooling blocks to fit within a space between the heating blanket and the heat sensitive material. The assembly of thermally conductive cooling blocks is then installed against the skin within the space, forming a heat sink that conducts a portion of heat out of the composite skin away from the heat sensitive material.

Methods for placing an indicia on a composite structure generally include printing the indicia on a first film surface of a coating film, with the coating film being in a partially cured state at the time the printing the indicia is performed, and positioning the coating film on a partially cured composite structure such that a second film surface of the coating film faces and is positioned against a surface of the composite structure, with the second film surface being opposite the first film surface. Finally, the coating film and the composite structure may then be co-cured. Systems for printing an indicia on a composite structure generally include the coating film, a printer configured to print the indicia on the first film surface of the coating film, a securement configured to secure the coating film during printing, and a curing device for co-curing the coating film and the composite structure.

The present invention relates to a V-ribbed belt in which a frictional power-transmission surface is formed from a weft knitted multilayer knitted fabric, characterized in that the weft knitted multilayer knitted fabric contains cellulose based natural spun yarn, polyester based composite yarn, and polyamide based yarn, and in that at least the cellulose based natural spun yarn and the polyamide based yarn are disposed in a layer on the frictional power-transmission surface side.

A method of preparing antimicrobial material sheets suitable for manufacturing a wide range of products having antimicrobial properties. In exemplary embodiments, a fabric having antimicrobial agents may be calendered with a polymer such as a silicone compound or an elastomer, in order to create a fused material sheet that contains the antibacterial properties of the fabric. In exemplary embodiments, the antimicrobial agent is copper, a copper alloy, silver, a silver alloy, or other suitable antimicrobial agent from which a fabric may be created. In some exemplary embodiments, an uncured silicone composition and copper alloy fabric are calendered to obtain an antimicrobial material sheet suitable for compression molding a wide range of products. In some exemplary embodiments, an uncured silicone composition and copper alloy fabric are calendered and roto-cured to obtain a cured antimicrobial material sheet or sheet rolls that maybe suitable for die-cutting.

A drip pan apparatus for a helicopter includes a frame and a drip pan. The frame is secured to a skirt on the airframe of the helicopter. The apparatus includes a drip pan for cooperation with a frame to cover an access opening to a transmission. The drip pan includes a substantially planar member of a fiber-reinforced composite and has a seal surface that is configured to cooperate with a seal surface of the frame. A seal member may be disposed between the substantially planar member and the frame to form a fluid-tight seal. The fiber-reinforced composite may be a carbon fiber-reinforced composite. A method of making the drip pan apparatus includes placing a plurality of sheets of an uncured fiber-reinforced composite material on one another to form an uncured stack. The uncured stack is then cured. A frame and a drip pan may be cut from the cured stack.

Prepregs having a UV curable resin layer located adjacent to a first thermally curable resin layer or sandwiched between first and second thermally curable resin layers wherein the UV curable resin layer is uncured or partially cured as well as methods for preparing laminates using the prepregs wherein the laminate includes at least one UV curable resin encapsulated electrical component.

A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness.