Abstract: A method for applying a thermal barrier coating according to at least one embodiment of the present disclosure includes: a step of forming a bond coat layer by high velocity flame spraying on a heat-resistant alloy base material of an object disposed in a thermal spray booth, with a thermal spray gun disposed in the thermal spray booth; and a step of forming a top coat layer by thermal-spraying a suspension containing ceramic powder by high velocity flame spraying on the bond coat layer of the object disposed in the thermal spray booth, with the thermal spray gun disposed in the thermal spray booth.

Abstract: A method of forming a ceramic matrix composite with being impregnated with molten metal includes: stacking a plurality of fiber layers that are layers of reinforced fibers impregnated with base resin to form a laminate in which a matrix layer containing fibers extending in a direction of impregnation with the molten metal is disposed between the fiber layers; forming an impregnation path in the matrix layer entirely in an in-plane direction perpendicular to a direction of the stacking in the laminate by carbonizing the formed laminate; and impregnating, with the molten metal, the laminate in which the impregnation path has been formed.

Abstract: An aircraft assembly having improved durability and capable of providing good lightning protection is provided. Provided is an aircraft assembly (1) equipped with an outer panel (5) that is constructed using an outer-panel resin material reinforced with fiber as a main element; a structural member (7) that supports the outer panel (5) from the inside; and a fastener (3) that joins the outer panel (5) and the structural member (7), the aircraft assembly including an insulator layer (23) having insulating properties and disposed so as to cover at least the head (17) of the fastener (3); and a conductor layer (25) disposed so as to cover at least the insulator layer (23) and formed of a conductor-layer resin material containing copper powder having electrical conductivity.

Abstract: An aircraft assembly having improved durability and capable of providing good lightning protection is provided. Provided is an aircraft assembly (1) equipped with an outer panel (5) that is constructed using an outer-panel resin material reinforced with fiber as a main element; a structural member (7) that supports the outer panel (5) from the inside; and a fastener (3) that joins the outer panel (5) and the structural member (7), the aircraft assembly including an insulator layer (23) having insulating properties and disposed so as to cover at least the head (17) of the fastener (3); and a conductor layer (25) disposed so as to cover at least the insulator layer (23) and formed of a conductor-layer resin material containing copper powder having electrical conductivity.

Abstract: A process for producing a metal member that enables both the fatigue properties and the corrosion resistance of the member to be improved, a structural member that includes a thus produced metal member, and a method of repairing a metal member. The process for producing a metal member comprises a projecting particles having an average particle size of not more than 200 ?m onto the surface of a metal material comprising an aluminum alloy using compressed air or a compressed gas, and a chemical conversion treatment including forming a film on the surface of the metal material by performing a chemical conversion treatment following projecting the particles.

Abstract: Surface processing of titanium alloy members for aerospace equipment imparts high wear resistance, lubricity and high fatigue strength. The method includes an oxygen diffusion step for causing oxygen to diffuse and penetrate in solid solution form into a surface of a titanium alloy member under an oxygen-containing gas atmosphere and a particle bombardment step for bombarding the surface of the titanium alloy member with an airflow containing particles. The aerospace equipment can include a flap rail member and slat rail member for aircraft.

Abstract: Provided are a method for forming a metal coating at high speed by using a simple cold spray apparatus, and an aerospace structural member on which a metal coating is formed by the cold spray method. In the metal coating forming method, nonspherical heteromorphous particles made of metal are projected onto a base material surface by the cold spray method to form a metal coating on the base material surface.

Abstract: A process for producing a metallic component of a structural member or the like used in an aircraft or automobile or the like, the process including shot peening the surface of a metallic material, wherein the fatigue properties of the metallic material are improved with almost no variation in the surface roughness over the course of shot peening. Shot peening the metallic material surface uses a shot material having an average particle size of not more than 200 ?m, and the ratio of the surface roughness of the metallic material surface following the projection step relative to the surface roughness of the metallic material surface prior to the projection step is not less than 0.8 and not more than 1.5.

Abstract: A process for producing a metallic component that includes shot peening the surface of a metallic material, wherein almost no dimensional change or roughening of the surface profile of the metallic material occurs, the iron fraction adhered to the surface of the metallic material is removed efficiently, and the fatigue properties of the produced metallic component are improved. First particles containing iron as the main component and having an average particle size of not less than 0.1 mm and not more than 5 mm are projected onto the surface of a metallic material containing a lightweight alloy, and second particles containing essentially no iron and having an average particle size of not more than 200 ?m are then projected onto the surface of the metallic material.

Abstract: A process for producing a metal member that enables both the fatigue properties and the corrosion resistance of the member to be improved, a structural member that includes a thus produced metal member, and a method of repairing a metal member. The process for producing a metal member comprises a projection step of projecting particles having an average particle size of not more than 200 ?m onto the surface of a metal material comprising an aluminum alloy using compressed air or a compressed gas, and a chemical conversion treatment step of forming a film on the surface of the metal material by performing a chemical conversion treatment following the projection step.

Abstract: A process for producing a metal member having improved fatigue life via a simple process. The process for producing a metal member comprises a burr removal step of removing burrs from the corners and edges of a metal member, and a projection step, which is performed after the burr removal step, without performing a chamfering treatment, of projecting particles having an average particle size of not less than 10 ?m and not more than 400 ?m onto a surface of the metal member.

Abstract: There is provided a fastener able to prevent damage due to environmental factors such as ultraviolet rays, and impact from sanddust, lumps of ice, and raindrops without obstructing a flow of electric shock current that flows along a top surface of an outer skin. The fastener connects an outer skin of an aircraft to a structural member positioned inside this outer skin, and is provided with a dielectric layer arranged to cover one end surface of a head section, and a conductive layer arranged to cover one end surface of this dielectric layer.

Abstract: An aircraft assembly having improved durability and capable of providing good lightning protection is provided. Provided is an aircraft assembly (1) equipped with an outer panel (5) that is constructed using an outer-panel resin material reinforced with fiber as a main element; a structural member (7) that supports the outer panel (5) from the inside; and a fastener (3) that joins the outer panel (5) and the structural member (7), the aircraft assembly including an insulator layer (23) having insulating properties and disposed so as to cover at least the head (17) of the fastener (3); and a conductor layer (25) disposed so as to cover at least the insulator layer (23) and formed of a conductor-layer resin material containing copper powder having electrical conductivity.

Abstract: A process for producing a metallic component that includes shot peening the surface of a metallic material, wherein almost no dimensional change or roughening of the surface profile of the metallic material occurs, the iron fraction adhered to the surface of the metallic material is removed efficiently, and the fatigue properties of the produced metallic component are improved. First particles containing iron as the main component and having an average particle size of not less than 0.1 mm and not more than 5 mm are projected onto the surface of a metallic material containing a lightweight alloy, and second particles containing essentially no iron and having an average particle size of not more than 200 ?m are then projected onto the surface of the metallic material.

Abstract: A metal coating with excellent adhesion is formed by a simple process on the surface of a formed article that comprises a resin, thereby imparting conductivity to the formed article. Metal particles are projected by a cold spraying method onto at least a portion of the surface of a formed article that comprises a resin, thereby forming a metal coating.

Abstract: A process for producing a metallic component of a structural member or the like used in an aircraft or automobile or the like, the process including shot peening the surface of a metallic material, wherein the fatigue properties of the metallic material are improved with almost no variation in the surface roughness over the course of shot peening. Shot peening the metallic material surface uses a shot material having an average particle size of not more than 200 ?m, and the ratio of the surface roughness of the metallic material surface following the projection step relative to the surface roughness of the metallic material surface prior to the projection step is not less than 0.8 and not more than 1.5.

Abstract: Provided is a surface processing of titanium alloy members for aerospace equipment having high wear resistance, lubricity and high fatigue strength. The method is characterized in that it comprises an oxygen diffusion step for causing oxygen to diffuse and penetrate in solid solution form into a surface of a titanium alloy member under an oxygen-containing gas atmosphere and a particle bombardment step for bombarding the surface of the titanium alloy member with an airflow containing particles. Also provided are a flap rail member and slat rail member for aircraft.

Abstract: There is provided a fastener able to prevent damage due to environmental factors such as ultraviolet rays, and impact from sanddust, lumps of ice, and raindrops without obstructing a flow of electric shock current that flows along a top surface of an outer skin. The fastener connects an outer skin of an aircraft to a structural member positioned inside this outer skin, and is provided with a dielectric layer arranged to cover one end surface of a head section, and a conductive layer arranged to cover one end surface of this dielectric layer.

Abstract: An inexpensive high temperature oxidation resistant material for spacecraft, having a higher heat resistance than a conventional oxidation resistant material of a silicon carbide coating system, which may be readily formed into a desired shape, a hot structure part including the oxidation resistant material for spacecraft, a spacecraft provided with the hot structure part, and a method for producing the oxidation resistant material for spacecraft are provided. The oxidation resistant material for spacecraft includes a ceramic material in which silicon carbide is included in zirconium boride. The method for producing the oxidation resistant material for spacecraft includes the steps of including SiC in zirconium boride, and molding by means of a normal pressure sintering method.

Abstract: An inexpensive high temperature oxidation resistant material for spacecraft, having a higher heat resistance than a conventional oxidation resistant material of a silicon carbide coating system, which may be readily formed into a desired shape, a hot structure part including the oxidation resistant material for spacecraft, a spacecraft provided with the hot structure part, and a method for producing the oxidation resistant material for spacecraft are provided. The oxidation resistant material for spacecraft includes a ceramic material in which silicon carbide is included in zirconium boride. The method for producing the oxidation resistant material for spacecraft includes the steps of including SiC in zirconium boride, and molding by means of a normal pressure sintering method.