The invention relates to a process for producing a coating film, optionally in the form of sheets or slabs, especially for the coating of a carrier layer (3), optionally textile materials and/or peelable polyurethane foams and/or a textile carrier layer (3), wherein the coating film (100) has an optionally multilayer upper layer (1) and a bonding layer (2) bonded thereto and optionally having multiple layers (2, 2) for bonding to the carrier layer (3).

It is envisaged in accordance with the invention that the bonding layer (2) creates an uncrosslinked, polyurethane layer having thermoplastic properties and having a thickness between 0.080 and 0.500 mm, preferably between 0.200 and 0.500, especially between 0.120 and 0.180 mm, and is bonded to the upper layer (1), and the upper layer (1) is a polyurethane layer which has a one-layer or preferably two-layer structure with an outer layer (1) and inner layer (1) and does not have thermoplastic properties, or a non-thermoplastic polyurethane layer which is amorphous or has a predominantly amorphous structure, said polyurethane layer being thinner than the bonding layer (2).

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 disclosure embraces cementitious panels, and systems and methods of manufacturing cementitious panels. An exemplary cementitious panel includes a cementitious core material, a plurality of sheets of facing material surrounding the cementitious core material, and a radiation-cured adhesive. An exemplary method of manufacturing a cementitious panel includes conveying a slurry of cementitious core material and a plurality of sheets of facing material, applying a radiation-curable adhesive to at least one of the sheets of facing material, forming a continuous length of cementitious panel material, at least partly curing the radiation-curable adhesive with one or more beams of radiation emitting from one or more radiation-emitting devices, and cutting the continuous length of cementitious panel material laterally to a desired length, providing a cementitious panel.

A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

The disclosure is directed to a method for producing a Fiber Metal Laminate component of an airplane, using a manipulator system with an end effector and a control, wherein at least one metal layer and at least one unhardened fiber layer are being stacked onto each other in a mould in a stacking sequence, wherein each stacking cycle comprises picking up a metal layer or a fiber layer from a supply stack according to the stacking sequence, transporting the layer to the mould, placement of the layer at a deposition surface in the mould and depositing the so placed layer onto the deposition surface. After being picked up from the supply stack and before being deposited onto the deposition surface the layer to be stacked can be deformed by the end effector as to adapt the form of the layer to the form of the deposition surface.

A method for manufacturing a sound-absorbing panel with a sandwich structure for reducing noise impact of an aeronautic engine includes providing a first skin of a thermoplastic polymeric material, making a plurality of micro-holes through the first skin by mechanical punching of the first skin, securing the first skin to a central layer by arranging a structural adhesive layer between the first skin and the central layer and/or by a thermal weld between the first skin and the central layer, and securing the central layer to a second skin by arranging a structural adhesive layer between the central layer and the second skin and/or by a thermal weld between the central layer and the second skin.

One or more layers of structured thermoplastic polymer, such as a light weight veil of thermoplastic polymer fibers, are located within the interleaf zone of laminates that are composed of fibrous layers and thermosetting resin. The thermoplastic veils are used in the interleaf zones as a replacement for thermoplastic toughening particles.

Prepregs having a UV curable resin layer located adjacent to a thermally curable resin layer wherein the UV curable resin layer includes at least one UV cured resin portion and at least one UV uncured resin as well as methods for preparing flexible printed circuit boards using the prepregs.

The present invention provides an oxidative polymerization resin-based composite coating film capable of being renewed a number of times by peeling a coating-film surface layer. More specifically, a coating composition comprising a base resin composition containing an oxidative polymerization resin; an organic compound having a melting point of 5 to 150 C.; a dryer; and an oxidative polymerization inhibitor containing at least one of a dryer protectant and a radical inhibitor is used to form a composite coating film made up of a cured film layer and an uncured inner layer.

An assembly of thermally conductive cooling blocks is configured to be placed against a composite skin between a heating blanket used to thermally cure a composite repair patch and a structure formed of a heat sensitive material. The cooling block assembly conducts heat away from the skin to prevent overheating of the heat sensitive material.