Mitsubishi Heavy Industries Limited

Masayuki Kanemasu

Kentaro Shindo

Toshio Kozasa

Shunichi Morishima

Hiromichi Akiyama

Hideki Horizono

Kazuki Noma

Shigeru Nishiyama

Noriya Hayashi

Hidetaka Hattori

Masayuki Yamashita

Akihisa Okuda

Makoto Hirai

Shuho Tsubota

Atsushi Yuge

Akihito Suzuki

Takehisa Okuda

Akira Kono

Atsumi Tanaka

Shigeyuki Matsubara

Hironori Maruyama

Kazuhiro Okada

Naoki Higuchi

Hiroshi Taneda

Shigeru Sakai

Kenichiro Abe

Susumu Ryuuou

Hirotoshi Hujigaki

Mikoto Omori

Kunihiko Shinoda

Yukari Sakuragi

Kensuke Sakaki

Tomoaki Inoue

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 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

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

An RTM molding device and an RTM molding method which enable resin impregnation of even large members and thick members without causing non-impregnated regions or fiber wrinkle, and yield a molded body having superior toughness and excellent precision. In the RTM molding device, a surface molding layer, which is disposed between a fiber-reinforced base material and a molding die, has a plurality of through-holes formed therein, and has sufficient rigidity that the thickness does not substantially change under the pressure inside the cavity when the inside of the cavity is placed under reduced pressure, and a resin diffusion portion, which is located on the side of the surface molding layer opposite the fiber-reinforced base material, and comprises a resin flow path formed so as to connect with the plurality of through-holes of the surface molding layer, are provided on at least one surface of the fiber-reinforced base material.

RTM molding device, RTM molding method, and semi-molded body

In manufacturing composite material by curing fluid, strength deterioration of the composite material due to repair before the fluid is cured is reduced. A suction hole is formed in a bag film () for sealing a space for fibers being impregnated with resin, after start of impregnation. The suction hole is covered by a plate () with holes (). The resin is sucked from the space through the plate (). According to such composite material manufacturing method, a defect, which occurs during fibers are impregnated with resin, can be repaired before the resin is cured without causing disorder and damage in the fibers. In a composite material formed from one repaired in the above way, the repaired portion is strong, namely, there is no strength deterioration due to repair after curing, and thus, the material is preferred as compared with a composite material which is repaired after resin is cured.

Composite material manufacturing device and composite material manufacturing method

A nondestructive inspection apparatus according to the present invention has a transmission-side probe configured to emit a first ultrasonic wave toward a test-target fluid, a plate through which a Lamb wave generated by the first ultrasonic wave is propagated when the first ultrasonic wave is propagated, and a reception-side probe configured to measure intensity of a second ultrasonic wave which is emitted from the plate and propagates through the test-target fluid. At this time, the nondestructive inspection apparatus can inspect the test-target fluid without bringing the transmission-side probe configured to emit the first ultrasonic wave and the reception-side probe configured to measure the second ultrasonic wave into contact with the test-target fluid.

Apparatus and method for nondestructive inspection

An object is to provide an impact-absorbing structure superior in impact-absorbing capacity. An impact-absorbing structure includes a pair of flat, plate-like face plates arranged to oppose each other with a predetermined distance therebetween; a core member arranged between the face plates and fixed to the face plates; and a composite-material tube arranged between the face plates, at the core member side, the impact-absorbing member extending in one direction and fracturing progressively due to an impact compression force acting in the one direction. The composite-material tube is fixed to the face plates at one portion constituting a bonded region and is allowed to move relative to the face plates at a remaining portion constituting a non-bonded region.

Impact-absorbing structure and method for producing the same

An impact-absorbing composite structure is formed with a resin and a fiber laminated body, and absorbs, when experiencing an impact, the impact by self destruction. An interlayer-strength improvement technique is applied on the impact-absorbing composite structure in an oblique manner or in a gradual manner.

Impact-absorbing composite structure

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Aichi, Japan

Masayuki Kanemasu