Mitsubishi Heavy Industries Limited

Toshio Kozasa

Shunichi Morishima

Masatake Hatano

Kazuaki Kishimoto

Masayuki Yamashita

Yukio Takeuchi

Hitoshi Ojika

Masayuki Kanemasu

Hiromichi Akiyama

Kazuki Noma

Masahiko Matsuhashi

Makoto Hirai

Kazuhiro Okada

Hiroshi Taneda

Toshihiko Azuma

Mikoto Omori

Yukari Sakuragi

Kensuke Sakaki

Kiyoshi Sugeta

Timothy Craig Momose

Takayuki Tani

It is an object of the present disclosure to provide an interior member for an aircraft, a manufacturing method of the member and a replacement method of the member in which replacement cost can be reduced. An interior member for an aircraft according to the present disclosure includes a substrate, a decorative layer that covers the surface of the substrate, and an adhesive layer that adheres to the decorative layer to the substrate, and the decorative layer is peelably pasted to the surface of the substrate via the adhesive layer in a range that meets a required adhesive strength and that does not affect the substrate.

Interior member for aircraft, manufacturing method of the same, and replacement method of the same

A composite material is capable of suppressing decrease in the strength, which is caused by bending of fibers of a skin material during the time when the composite material is cured. A composite material is provided with a honeycomb core, a first skin material, a second skin material, a thunder-resistant mesh and a resin material; and the resin material is not arranged in a neighborhood portion which is the region corresponding to the region at the front end of the honeycomb core. A first film adhesive is arranged between the first skin material and the honeycomb core; a second film adhesive is arranged between the second skin material and the honeycomb core; and a fourth film adhesive is arranged in the neighborhood portion of the resin material in a weight per square meter, which is lower than those of the first film adhesive and the second film adhesive.

Composite material and method for curing composite material

A pultrusion material serves as a composite material having a reinforced part that is a part reinforced against a load acting in a load direction. The reinforced part includes: a core material that comprises bundled reinforcing fibers and that is provided so as to extend along the load direction; and a cover section obtained by covering the circumference of the core material with a fiber sheet. The fiber direction of the reinforcing fibers in the core material is oriented along the load direction.

Composite material, pultrusion device, and pultrusion method

A method is for manufacturing a honeycomb structure including a core material in which a hole is formed to penetrate in a thickness direction and is arranged in a plane direction, and a skin material that is stacked on a surface of the core material. The skin material includes a thermosetting resin. The method includes half-curing the thermosetting resin by placing the skin material in a bag and heating the skin material in a state where an inside of the bag is evacuated and an outside of the bag is under an atmospheric pressure; stacking the skin material in which the thermosetting resin is half-cured onto a side of the surface of the core material; and bonding and integrating the core material and the skin material with each other by pressurizing and heating the stacked core material and skin material with the use of a sealing pressurizing heating facility.

Method for manufacturing structure, method for preparing skin material, and method for setting heating condition for skin material

A method for designing the cross-sectional shape of the fuselage of a flying body having the fuselage extending in the roll axial direction, the section being taken on a plane perpendicular to the roll axial direction. This method is provided with: an initial setting step Sfor setting an initial cross-sectional shape, which is the initial cross-sectional shape of the fuselage having a cross-sectional shape that is not truly circular; load application steps S, S, Sfor analytically or experimentally preloading the fuselage having the initial cross-sectional shape; and a design shape setting step Sfor acquiring the cross-sectional shape of the preloaded fuselage as the design cross-sectional shape of the fuselage.

Method, design device, and design program for cross-sectional shape of fuselage

The present invention addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure that is high-quality, low cost, and leaves less voids. The present disclosure addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure with which it is possible to reduce dimples in a composite material skin at low cost. According to a method for molding a composite material structure of the present disclosure, an uncured composite material honeycomb sandwich panel in which prepreg is laminated on upper and lower surfaces of a honeycomb core via an adhesive is covered with a vacuum bag and placed in an autoclave. After that, the vacuum bag is evacuated and, while the evacuation is being continued, is heated and pressurized by the autoclave to cure a matrix resin of the prepreg and achieve adhesion to the honeycomb core.

Method for molding composite material structure

Provided are a method and a device for producing a pultruded material that improve the homogeneity of a thermosetting resin. The device for producing a pultruded material comprises a first opening section, a second opening section, a closing section, a tension-applying section, an impregnating section, and a mold. The first opening section and the second opening section open a bundle of reinforcing fibers and thereby obtain a bundle of reinforcing fibers. The closing section closes the bundle of opened reinforcing fibers and thereby obtains a bundle of reinforcing fibers. The tension-applying section applies tension along the direction in which the reinforcing fibers extend to the bundle of reinforcing fibers that pass through the closing section. The impregnating section impregnates the bundle of reinforcing fibers with a thermosetting resin. The mold pultrudes the bundle of reinforcing fibers that have been impregnated with the thermosetting resin.

Method and device for producing pultruded material

A joined member assembly method includes: a step in which a substrate is inserted in a gap between a superposed first component and a second component, said substrate being configured from a multilayer fabric that is capable of expanding as a result of heating and that is flexible after expansion and a reinforcing material woven into the multilayer fabric; a step in which the substrate is heated and made to expand in the thickness direction; a step in which the gap is filled with a resin and the substrate is impregnated with the resin; and a step in which the resin is cured. A step in which a seam is created by machining in accordance with a measured gap shape is omitted.

Joined member assembly method and joined member

A device for producing a pultruded article is provided with: a mold in which an intermediate molded article comprising reinforcing fibers impregnated with a thermosetting resin is heated and hardened; and a pultrusion device that causes a pultruded article generated by heating and hardening the intermediate molded article in the mold to be pultruded from the mold. The mold comprises a pressing member that is elastically deformable and that presses the intermediate molded article.

Device and method for producing pultruded article

This pultrusion material that is a composite material member comprises: a plurality of fiber sheets that extend along a lengthwise direction; and a gap material that is provided to a gap formed by the plurality of fiber sheets, wherein the gap material has a gap fiber sheet including reinforcement fibers that are oriented in a different fiber direction than the lengthwise direction, and has gap reinforcement fibers that are oriented in the same fiber direction as the lengthwise direction. Additionally, the gap reinforcement fibers are provided evenly distributed in a cross-section of the gap material, said cross-section being perpendicular to the lengthwise direction.

Composite material member, gap material, pultrusion device, and pultrusion method

Provided are: a fiber-containing material which has improved strength in an out-of-plane direction without a decrease in strength in an in-plane direction; a method for inserting out-of-plane reinforcement threads; and a method for producing the fiber-containing material. The fiber-containing material contains a base material and out-of-plane reinforcement threads. The base material contains reinforcement fibers extending in a direction along a plane. The out-of-plane reinforcement threads are formed in the base material so as to extend in a direction intersecting the direction along the plane.

Method for inserting out-of-plane reinforcement threads and method for producing fiber-containing material

A method for producing a pultruded article includes: a step in which an activation sheet having a sliding surface capable of sliding with the inner surface of a mold is arranged on the surface of an intermediate molded article comprising reinforcing fibers that are impregnated with a thermosetting resin and the intermediate molded article and the activation sheet are introduced into a mold together; and a step in which a pultruded article generated by heating and hardening the intermediate molded article in the mold is pultruded together with the activation sheet from the mold.

Production method for a pultruded article

This device for producing a pultrusion molded article is provided with: a mold member that heats and cures an intermediate molded article as a result of the mold member contacting an intermediate molded article in which reinforcing fibers are impregnated with a thermosetting resin; a pultrusion device for extracting, in the pultruding direction, the pultrusion molded article formed by heating and curing the intermediate molded article; and a moving device for moving the mold member in the pultruding direction in synchronization with the pultrusion device.

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Tokyo, Japan

Toshio Kozasa