Mitsubishi Heavy Industries Limited

Mitsubishi Aircraft Corporation

The Society of Japanese Aerospace Companies

Japan Aviation Electronics Industry, Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Osaka University

Riken Corporation

Tokyo Institute of Technology

Otowa Electric Co., Ltd.

Mitbushi Aircraft Corporation

Yuichiro Kamino

Nobuyuki Kamihara

Toru Hashigami

Naomoto Ishikawa

Masahiro Bessho

Ichiro Yamashita

Hiroaki Yamaguchi

Ikuo Wakamoto

Koichi Nakamura

Atsushi Tanaka

Hiroshi Ogawa

Hideo Yamakoshi

Toshio Abe

Kazumasa Mihara

Toshikatsu Nohara

Atsuhiro Iyomasa

Masayuki Yamashita

Kazuaki Kishimoto

Koji Kawahara

Wataru Nishimura

Yasunori Watanabe

Takashi Sonoda

Tatsufumi Aoi

Keiichi Morishita

Kazuyuki Oguri

Tooru Hashigami

Tamaki Tsuzuki

Kenji Hara

Akihisa Okuda

Hisashi Tanaka

Akiko Inoue

Akira Ikada

Masahiro Kashiwagi

Hiroaki Minamide

Mikio Kozuma

Susumu Urano

Ryotaro Inoue

Yuji Asahara

Takahiro Sekigawa

Syusaku Yamamoto

Kazunori Yoshioka

Takeyasu Tarumi

Etsuro Hirai

Hidekazu Ono

Kazuhiro Tsukuda

Tomonori Okumura

Sadao Miura

Masaki Kitaoka

Keisuke Kajikawa

Koji Nawata

Mitsuo Naruse

Masashi Ooya

Naoki Hisanaga

Takahisa Masukawa

Toshiyuki Tajima

Seiichi Morimoto

Takashi Mukaiyama

Makoto Senda

Wataru Nihimura

Hiroki Makimura

Koki Higashide

Kohei Murakami

Naotatsu Ishimaru

Utako Tanaka

Yoko Koyanagi

An inspection device includes: a light source for outputting pulsed excitation light with a time width of 10 picoseconds to 10 nanoseconds; a nonlinear optical crystal for generating a terahertz wave by optical wavelength conversion of the pulsed excitation light; a polarization part for reflecting at least a part of a reflected wave of the terahertz wave reflected by an inspection target; and a detector for detecting the reflected wave reflected by the polarization part.

Inspection device

The present invention reduces measurement time. A gyroscope of the present invention includes a planar ion trap part, a microwave irradiation part, a laser irradiation part and a measurement part. The planar ion trap part includes two rf electrodes and two DC electrode rows, and forms ion traps that trap one ion on a substrate, a normal direction of the surface of the planar ion trap part corresponds to a z direction. The rf electrodes are disposed in the x direction on the substrate at a predetermined interval. The DC electrode rows are disposed in the x direction on the substrate so as to sandwich the two rf electrodes. The DC electrode rows each include at least five DC electrodes in the x direction. The trapped ions are spaced so as not to interfere with each other. The microwave irradiation part irradiates the ions with &#x3c0;/2 microwave pulses.

Gyroscope and angle measurement method

An insulative ring protects a burst disc of an aircraft from the shock of lightning strikes. The burst disc device includes: a burst disc which is installed inside a main wing to prevent over-pressurization of the main wing; a pressure release passage partially constituted by a support tube and is blocked with the burst disc and leads to the outside of the main wing; an insulative ring which is disposed along the inner peripheral edge at a terminal end of the pressure release passage and exposed to the outside of the main wing, and an insulation layer which is disposed between a flange of the support tube and an inner surface of a panel of the main wing.

Burst disc device and aircraft

A cap is applied to a securing structure part for securing structure elements using a fastener passed through through-holes formed in the structure elements, and a collar fastened to the tip part of the fastener. A filler engaging part for engaging a cured filler, configured with a female thread that turns about a center axis, is formed on the inner peripheral surface of the cap. The filler engaging part includes a first helical engagement part formed in the region near the cap inner part of the inner peripheral surface in the center axis direction; and a second helical engagement part formed in the region near the cap opening-end part in the center axis direction, the inner diameter of the second helical engagement part being greater than that of the first helical engagement part, and having a helical direction that is opposite to that of the first helical engagement part.

Cap and securing structure part using cap

The purpose of the present invention is to provide a fuel tank, main wings, an aircraft fuselage, an aircraft, and a moving body, which enable working hours and costs involved in a manufacturing process to be reduced, and weight increases to be prevented. The fuel tank includes a structural member in which carbon fiber reinforced plastic (CFRP) is used, the carbon fiber reinforced plastic (CFRP) including a reinforcing material that includes carbon fibers and a matrix that includes plastic. The structural member is formed by laminating a conductive sheet between prepregs of the carbon fiber reinforced plastic (CFRP). In this case, a cut surface of the structural member formed by cutting the structural member may be exposed on the inside in which fuel is stored.

Fuel tank, main wings, aircraft fuselage, aircraft, and moving body

A fuel tank in which it is possible to reduce working hours or cost in a manufacturing process and prevent an increase in weight in, a main wing, an aircraft fuselage, an aircraft, and a mobile body. The fuel tank is provided with a structural member using carbon fiber reinforced plastic in which a reinforcing material includes carbon fibers and a matrix includes plastic, wherein the matrix has electrical conductivity applied thereto. Furthermore, a cut surface of the structural member, which is formed by cutting the structural member, may be exposed to the inside in which fuel is accommodated, of a fuel tank.

Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body

The purpose of the present invention is to provide: a structural material for structures which is capable of attaining reductions in working time and cost in production steps and of preventing an increase in weight; a fuel tank; a main wing; and an aircraft. A rib () as the structural material for structures is characterized by comprising a carbon-fiber-reinforced plastic wherein the reinforcement comprises carbon fibers and the matrix comprises a plastic, and the surface of the carbon-fiber-reinforced plastic was coated with a low-viscosity surface-protective material () having conductivity imparted thereto.

Structural material for structure, fuel tank, main wing, and aircraft

There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A holeis formed in a cap, and a screw grooveis formed in the hole. The configuration enables the capto be reliably and easily positioned and installed on a fastener memberand reliably prevents the capfrom coming off after the installation thereof. This improves the workability to reduce the production cost while assuring sufficient insulation properties and enables the capto be installed with stable quality irrespective of workers. Preferably, the capis made of a resin in view of mass producibility, weight reduction, and the like.

Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener

A fuel gauge () provided with an inner structural body () that is formed of an insulator; an outer structural body () that is formed of an insulator and disposed on the outer circumference side of the inner structural body () over the entire circumference thereof; an inner electrode () that is attached to an outer circumferential surface of the inner structural body (); and an outer electrode () that is attached to an inner circumferential surface of the outer structural body (). The fuel guage measures the capacitance between the inner electrode and the outer electrode and detects the level of fuel that exists between the inner electrode and the outer electrode. The outer structural body is provided with a plurality of outer through-holes () that allow electric charge to move from an outer circumferential surface thereof to the outer electrode.

Capacitive level gauge

A composite tank that can suppress electrification, corrosion and strength degradation, a wing comprising the composite tank, and a method for manufacturing the composite tank. The composite tank comprises: a tank body inside which a combustible material is stored, having a first resin portion () formed from a fiber reinforced resin and a metal portion formed from a metal material, a second resin portion () formed from a fiber reinforced resin, which covers at least those regions on the inner surface of the tank body where the first resin portion () adjoins the metal portion, and a plurality of conductive portions () that enable charge transfer through the second resin portion (), from the surface that contacts the combustible material to the first resin portion (), wherein the fiber in the second resin portion () has a higher electrical resistivity than fiber in the first resin portion (), and the second resin portion () forms a layer that isolates the first resin portion () from the metal portion.

Composite tank, wing, and method for manufacturing composite tank

Even when a large-current, high-voltage load is applied, damage is prevented. A current generating device () supplies a current simulating a current flowing when lightning occurs to a test piece () subjected to a lightning resistance test using power supplied from a power supply device (). The current generating device () includes electric double-layer capacitors that store and discharge power supplied from the power supply device (), a semiconductor switch () that switches between supplying and not supplying the power stored in the electric double-layer capacitors to the test piece (), and a protection unit () that is connected between the semiconductor switch () and the test piece () and that cuts the connection between the semiconductor switch () and the test piece () when a current larger than a predetermined value flows through the semiconductor switch ().

Current generating device

Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern partmade of a conductive material is formed around each fastener memberbetween wing surface panelsA andB. The conductive pattern partis formed, for example, around each of holesandon the plane on which the wing surface panelA and the wing surface panelB abut against each other. Then, the conductive pattern partis pushed against both the wing surface panelA and the wing surface panelB by the fastening power of the fastener members, whereby electrical conduction between the wing surface panelA and the wing surface panelB can be achieved.

Coupling structure for airframe components

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

Growing community of inventors

Tokyo, Japan

Yuichiro Kamino