Mitsubishi Aircraft Corporation

Mitsubishi Heavy Industries Limited

Masayoshi Suhara

Shuhei Muto

Toshikazu Shigetomi

Morimasa Ishida

Kiwamu Arikawa

Hiroyuki Iseki

Hiromu Okamoto

Ryuichi Nagase

Hideaki Tanaka

Kunihiro Morishita

Kohei Hatano

Katsumi Takagi

Ryosuke Hashizume

Provided is a composite material assembly () includes: a first composite material member () in which a first hole () is formed, a second composite material member () in which a second hole () is formed, and a fastener () that is to be inserted through the first hole () and second hole () to thereby connect the first composite material member () to the second composite material member (). A first chamfered section (C) is formed on at least one of both ends of the first hole (), and a second chamfered section (C) is formed on at least one of both ends of the second hole ().

Composite material assembly

An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.

Aircraft reinforcing structure

To reduce a time required for repairing a honeycomb core sandwich panel. A repair method according to the present invention is a repair method, in which a repair patchis disposed on a repair target portion that exists on the side of a repair surfaceA of a honeycomb core sandwich panel, the honeycomb core sandwich panelbeing formed by sandwiching a honeycomb structured corewith a plurality of cells between skinsand, the method including: a heating step of heating the repair patch; and a cooling step of cooling the honeycomb core sandwich panelfrom the side of a second surfaceB opposing the repair surfaceA of the honeycomb core sandwich panel

Method and apparatus for repairing honeycomb core sandwich panel

The present invention sufficiently heats a repairing material while preventing change in quality of a base material provided with the repairing material so as to securely bond the repairing material to a repair target portion. The repair method of the present invention, in order to repair a repair target portionexisting in an outer panel, includes: a repairing material disposing step of disposing a repairing patchincluding a resistance heating elementand a carbon fiber reinforced resin, and an adhesiveA including a thermosetting resin before being hardened for bonding the repairing patchon the repair target portion; and a heating-hardening step of heating and hardening the thermosetting resin of the adhesiveA by causing the resistance heating elementto generate heat through supply of electricity thereto.

Repair method of repair target portion, repaired product, and repair apparatus

The present invention provides a device which can uniformize heat distribution by using an existing heater mat for repairing or joining members. A heat dispersion device includes a bag with a fluid sealed inside, and is disposed on a second surface of a heater mat which has a first surface to be directed toward an object to be heated and the second surface opposite to the first surface. The fluid inside the bag is preferably heated with a heat source.

Heat dispersion device and repair and joining methods

The present invention provides a method for repairing a lightning protection material that is made of a metal material and is provided along a surface of a member formed by using a fiber reinforced resin includes: bonding a repair material made of a metal material over a lost region of the member where the lightning protection material is lost by using a liquid adhesive and a sheet-shaped holder that contains and holds the adhesive and is arranged at the lost region.

Method for repairing lightning protection material, and member provided with lightning protection material

To provide a structure maintenance supporting system that can accurately and quickly associate any position on a structure with a position in the drawing of the structure that is referred to at the time of maintenance. A maintenance supporting system includes an image displaying device that displays an image of a structure to be referred to when any damaged position on the structure is maintained, and a processing unit that performs calculation to associate the damaged position with a position in the image. The processing unit includes a damaged position calculating section that calculates a target coordinate which is the coordinate of the damaged position using known coordinates given to a plurality of reference points, and a position specifying section that specifies a position in the image corresponding to the target coordinate with an indication on the image displaying device.

Maintenance supporting system and maintenance supporting method utilizing a reference image and indicator

There is provided a drainage system of an aircraft which discharges moisture having entered inside horizontal tails, which are structures of an airframe of an aircraft, toward the rear end of a fuselage, the drainage system including: a drainage channel which includes an introduction end and a discharge end, and by a capillary action delivers moisture introduced from the introduction end toward the discharge end; and a heater which heats and dries the moisture delivered through the drainage channel. The drainage channel of the present invention is preferably composed of a paper drainage material. It is also preferable that the introduction end of the drainage channel is provided in a lowermost region in the vertical direction within an area in which moisture can accumulate inside the horizontal tails while the aircraft is parked.

Drainage system

The present invention sufficiently heats a repairing material while preventing change in quality of a base material provided with the repairing material so as to securely bond the repairing material to a repair target portion. The repair method of the present invention, in order to repair a repair target portionexisting in an outer panel, includes a repairing material disposing step of disposing a repairing patchand an adhesiveA to the repair target portion; and a heating-hardening step of heating and hardening the adhesiveA by irradiating it with electromagnetic waves.

Repair method of repair target portion, and repair apparatus

The present invention relates to a repair method using a pre-cured repairing patch, and a repaired product obtained from repairing using the repairing patch, and the present invention securely bonds a repairing patch, where an out-of-plane stiffness is required, to a repair target. In order to cover a repair target portionformed in an outer panelwith a repairing patch, and bond the repairing patchto a repair target, repairing platesthat are formed of fibers and thermosetting resin, and pre-cured before repairing are used as the repairing patch, and a laminating step Sof laminating the repairing plates, and a bonding step Sof bonding the repairing platesto each other are performed.

Repair method of repair target portion, and repaired product obtained from repairing

A repair method according to the present invention is a method for repairing a honeycomb core sandwich panel, the method including: a repair patch disposing step of disposing a repair patch and an adhesive on at least one of a first surface and a second surface of the panel, the first outer skin being located on the first surface, and the second outer skin being located on the second surface; a panel restraining step of sandwiching the panel and the repair patch from both surface sides of the first surface and the second surface and thereby restraining the panel; and a heating step (thermal curing step) of heating the adhesive while the panel is restrained.

A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step Sof removing a damaged partfrom the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step Sof sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step Sof placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step Sof evacuating in a state in which the front side is sealed.

Growing community of inventors

Tokyo, Japan

Masayoshi Suhara