Mitsubishi Heavy Industries Limited

The Society of Japanese Aerospace Companies

Fujiwara, Co., Ltd.

Kazuyuki Oguri

Takahiro Sekigawa

Yuichiro Kamino

Akiko Inoue

Koichi Nakamura

Hiroaki Yamaguchi

Tooru Hashigami

Takayuki Takahashi

Hideo Yamakoshi

Naomoto Ishikawa

Masahiro Bessho

Masahiro Kashiwagi

Takashi Kimura

Takeyasu Tarumi

Katsuto Okada

Makoto Senda

An aircraft window member includes film made of acrylic resin, a conductive mesh, which is formed on the film and in which a conductive material, is formed in a mesh shape so as to have optical transparency for ensuring visibility and to have electromagnetic-wave shielding properties, and a window main body, which is made of acrylic resin, and to which the film on which the conductive mesh is formed is attached.

Aircraft window member, method of manufacturing the same, and aircraft window assembly

An aircraft fuel tank that is capable of suppressing the occurrence of sparks on a pipe caused by a lightning current through the pipe during a lightning strike, and also suppressing static electricity charging of a pipe caused by flow electrification generated by the fuel. An aircraft fuel tank () in which a storage section is formed using a conductive upper skin (), a conductive lower skin () and conductive spars (), the tank comprising: pipes inside the tank, such as a refuel pipe (), an engine feed pipe () and an inert gas pipe (), which are disposed inside the storage section and are earthed () at a plurality of locations, and pipe outer surface layers () having semiconductor properties that are formed in an integrated manner on the outer surfaces of the pipes inside the tank such as the replenishing pipe (), the supply pipe () and the gas pipe ().

Aircraft fuel tank

A lightning-protection fastener is provided that is capable of reliably preventing peeling off of an insulation layer during the operation of an aircraft and improving the anti-lightning-strike capability and reliability. There is a lightning-protection fastener that fastens a skin of an aircraft and a structural member positioned inside the skin, in which an insulation layer is melt adhered so as to cover one end surface of a head portion and also to mechanically engage with a fastener-side engagement portion (engagement portion) formed on the end surface.

Lightning-protection fastener

An aircraft fuel tank capable of suppressing electrostatic charging caused, for example, by flow electrification with the fuel. The aircraft fuel tank comprises an upper skin () and a lower skin () that exhibit conductivity and form a portion of a container for storing fuel, an internal structure () formed from a metal, and an inner surface layer () which has semiconductor properties or insulating properties and is formed in an integral manner on the inner surfaces of the upper skin () and the lower skin () in a location where the internal structure () contacts the upper skin () and the lower skin (), and in the surrounding portion thereof, wherein the inner surface layer () is formed, at least in the surrounding portion, from a material having semiconductor properties.

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

Aircraft assembly and method for manufacturing the same

An aircraft assembly is equipped with a lightning protection structure that is not easily destroyed by lightning current and that is highly reliable. The aircraft assembly includes a skin in which a CFRP layer serves as a main structure, a shear-tie that supports the skin from the inside, and a fastener that couples the skin and the shear-tie. A copper foil and an outside GRFP layer are provided on an outer surface side of the skin, in this order towards the outside, and a copper paint layer, which contains copper powder, is provided on the outside GFRP layer.

Aircraft assembly

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 &#x3bc;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.

Process for producing metal member, structural member with thus produced metal member, and method of repairing metal member using shot peening

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.

Surface treatment for titanium alloy member for aerospace equipment

A fastener, of which severe strength is demanded and which can also be applied to a location, in which a flush surface equipment is taken into consideration, and which can be manufactured readily and quickly and reduced in manufacturing cost, is provided. A fastener () joins a skin of an airplane and a structural material positioned inside the skin and one end surface of a flush head () is covered by an insulator layer ().

Fastener

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 &#x3bc;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.

Process for producing metallic component and structural member

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 &#x3bc;m are then projected onto the surface of the metallic material.

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.

There is provided a method of manufacturing a window having at least one of a radio wave stealth property and an electromagnetic wave shield property comprising: a step for forming a thin-film composed of a conductive material on the surface of a transparent window member having a curved surface, and a step for forming the thin-film into a mesh shape. As a result, it is, possible to manufacture, at lower cost, a window having a radio wave stealth property that scatters radio waves in various directions so as not to be detected by radar, while transparency to visible light is improved, as well as a window having an electromagnetic wave shield property that effectively prevents harmful electromagnetic waves, except for visible radiation, from invasion into an aircraft.

Method of manufacturing window having at least one of radio wave stealth property and electromagnetic wave shield property, and window material having at least one of radio wave stealth property and electromagnetic wave shield property

An aircraft window of synthetic resin has a hard coated film and either at least a double-pane or single-pane construction, the hard coated film comprises siloxane bonds and/or silazane bonds obtained obtained by coating a coating composition containing perhydropolysilazane or its condensation polymer which is substantially soluble in organic solvent on the surface of the synthetic resin aircraft window and heat-treating at approximately ambient temperature to 100&deg; C. in air or humidified air.

Aircraft window of synthetic resin having hard coated film and a method for producing the same

A high temperature oxidation resistant coating performs a self-repairing function of self-repairing the cracks under a heated environment and has low catalytic properties. The high temperature oxidation resistant coating is prepared by dispersing silicate particles containing a composite oxide consisting of an oxide of a lanthanoide series rare earth element including yttrium and silicon oxide into a glass-based matrix.

Growing community of inventors

Nagoya, Japan

Kazuyuki Oguri