A synthetic polymer film whose surface has a plurality of raised or recessed portions, wherein a two-dimensional size of the plurality of raised or recessed portions is in a range of not less than 0.5 μm and not more than 3 μm when viewed in a normal direction of the synthetic polymer film, the synthetic polymer film has a crosslink structure and contains an organic carboxylic acid, at the lapse of 5 minutes since placing a 200 μL drop of water on the surface of the synthetic polymer film, a pH of an aqueous solution is less than 4, and an area equivalent circle diameter of the aqueous solution is not less than 20 mm, and at the lapse of 60 seconds since placing a drop of water on the surface of the synthetic polymer film, a static contact angle of the water drop with respect to the surface is less than 3°.

The present invention generally relates to a system and method for using a volatile organic compound (VOC) free low radiant flux LED UV curable composition, and more particularly to unique and novel uses of the composition such as one or two or more of a fire retardant, clear coat, composite material, resin, top coat, improved holdout coating, a sealant coat, and combinations of the same.

An anti-sticking agent composition for an unvulcanized rubber of the present disclosure includes the following components (A) to (C), and water is provided. The component (A) contains the following component (A1) and the following component (A2). The component (A) is water-soluble polymer, the component (B) is metallic soap, the component (C) is surfactant, the component is (A1) water-soluble polymer other than the component (A2), and the component (A2) is non-ionic cellulose ether.

Described herein is a manual process for injection molding of coated components, more particularly coated soles of plastic, where first of all the molding tool is lined with a release agent composition and, after flashing of this release agent composition, a composition for forming the component is injected. After crosslinking of these two compositions, the produced coated component is removed from the molding tool and subjected optionally to an aftertreatment.

Described herein is an automatic or automated process for injection molding of coated components, more particularly coated soles of plastic, where first of all the molding tool is lined with a release agent composition and, after flashing of this release agent composition, a composition for forming the component is injected. After crosslinking of these two compositions, the coated component produced is removed from the molding tool and subjected optionally to an aftertreatment.

Embodiments relate to a method of fabricating a nano-sized structure in a resin element by nanoimprint lithography (NIL). The method reduces adhesive failure during NIL demolding by inhibiting polymerization at the interface between the resin element and the template. The template includes a polymerization inhibiting compound. The method includes pressing the template onto the resin element (or the resin element onto the template) to form the nano-sized structure in the resin element. The method also including diffusing the polymerization inhibiting compound from the template to the resin element, e.g., by holding them together for a period of time. A layer of the polymerization inhibiting compound is therefore formed at an interface of the template and resin element. The polymerization inhibiting compound inhibits polymerization at the interface. After the diffusion, the resin element is cured. Then the template is removed from the resin element.

A method for fabricating aircraft engine external target parts including complex geometries utilizes reusable reconfigurable shape memory polymer and conformable woven braided carbon fiber sleeves. The method includes providing a tubular three-dimensional reusable shape memory polymer mandrel assembly designed for a target part, and heating the shape memory polymer mandrel.

A novel cutting-edge structure and method and apparatus for manufacturing the cutting-edge structure is provided. The cutting-edge structure is comprised of naturally derived or renewable material at greater than 50% by volume fraction. In one embodiment, the naturally derived material is a cellulose nanostructure such as a cellulose nanocrystal. The cellulose nanocrystal is processed using a base or mold structure to provide a cutting edge of any shape such as linear or circular edge structures. The process includes dual cure steps to produce an optimal cutting-edge structure without shrinkage. The formed cutting-edge structure can be utilized as a razor blade as it is formed with very sharp tip and edge suitable for cutting hair. The base structure can form one or more cutting-edge structures simultaneously.

A system and method for continuous additive manufacturing of objects is provided. The system includes a container configured to receive a photopolymer and a print bed disposed within the container. An first end effector is movably disposed within the container. A light source is operably coupled to the first end effector, the light source being configured to emit and electromagnetic radiation. Wherein at least one of the print bed or first end effector is movable relative to the other to perform continuous separation curing of the photopolymer on the print bed with the electromagnetic radiation.

Embodiments of the present disclosure generally relate to protective coatings on an aerospace component and methods for depositing the protective coatings. The protective coating can be anti-coking coatings to reduce or suppress coke formation when the aerospace component is heated in the presence of a fuel. In one or more embodiments, a method for depositing the protective coating on an aerospace component includes exposing the aerospace component to a cleaning process to produce a cleaned surface on the aerospace component and sequentially exposing the aerospace component to a precursor and a reactant to form a protective coating on the cleaned surface of the aerospace component by an atomic layer deposition (ALD) process. The aerospace component can be one or more of a fuel nozzle, a combustor liner, a combustor shield, a heat exchanger, a fuel line, a fuel valve, or any combination thereof.