Abstract: 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 (11) 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 (18) having conductivity imparted thereto.

Abstract: 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.

Abstract: Even when a large-current, high-voltage load is applied, damage is prevented. A current generating device (1) supplies a current simulating a current flowing when lightning occurs to a test piece (9) subjected to a lightning resistance test using power supplied from a power supply device (2). The current generating device (1) includes electric double-layer capacitors that store and discharge power supplied from the power supply device (2), a semiconductor switch (3) that switches between supplying and not supplying the power stored in the electric double-layer capacitors to the test piece (9), and a protection unit (4) that is connected between the semiconductor switch (3) and the test piece (9) and that cuts the connection between the semiconductor switch (3) and the test piece (9) when a current larger than a predetermined value flows through the semiconductor switch (3).

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: An object of the invention is to provide a structural material for a structure which enables a reduction in weight, while reducing the time and effort required during production and ensuring favorable lightning resistance performance. The structural material for a structure comprises a carbon fiber reinforced plastic in which the reinforcing material comprises a carbon fiber, the matrix comprises a plastic, and the resistivity in the sheet thickness direction is at least 1 ?cm but not more than 200 ?cm. The carbon fiber reinforced plastic may have a resistivity in the thickness direction of not more than 100 ?cm, and a metal foil or a metal mesh may be provided on the surface of the carbon fiber reinforced plastic.

Abstract: 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.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: An object is to emit x-rays having a plurality of different energies and to suppress variations in the energy of the created x-rays. In an x-ray generating apparatus (14) provided in an x-ray inspection apparatus (10), a particle accelerator (20) creates a charged particle beam for generating x-rays having a plurality of different energies, and x-rays are emitted by irradiating a target (22) with the charged particle beam. A single-energy control device (40) controls the particle accelerator (20) for each of the x-rays having different energies on the basis of an x-ray radiation level per unit target current obtained from a measured value of the current flowing in the target (22) and a measured value of the radiation level of x-rays emitted from the target (22), when the target (22) is irradiated with the charged particle beam.

Abstract: 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 (1) in which a storage section is formed using a conductive upper skin (5), a conductive lower skin (7) and conductive spars (9), the tank comprising: pipes inside the tank, such as a refuel pipe (17), an engine feed pipe (19) and an inert gas pipe (21), which are disposed inside the storage section and are earthed (27) at a plurality of locations, and pipe outer surface layers (31) 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 (17), the supply pipe (19) and the gas pipe (21).

Abstract: An X-ray generating device (10) is provided with an electron gun (12) that generates an electron beam, a linear accelerator (14) that accelerates, by means of microwaves, the electron beam generated by the electron gun (12), an X-ray target (16) that generates X-rays by being irradiated with the electron beam accelerated by the linear accelerator (14), a microwave generating device that generates microwaves to be introduced into the linear accelerator (14), and a pulse modulator that controls the microwave generating device so as to change the power of the microwaves. Because the linear accelerator (14) includes a plurality of buncher cavities (40), even if there are electrons that are shifted out of the acceleration phase when the power of the microwaves is decreased, these electrons can be accelerated in the acceleration phase of the next time period; therefore, a decrease in the intensity of an electron beam to be emitted is suppressed even if the power of the microwaves is decreased.

Abstract: 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.

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high reliability. A ring-shaped ring member 40A made of resin is mounted on a collar 26. This ring member 40A is interposed between a member 22 and the collar 26 and is in intimate contact with both of the member 22 and the collar 26, thereby sealing an interface with the member 22 for sealing and preventing the occurrence of an arc at an outer perimeter edge of the collar 26.

Abstract: 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 (5) and a lower skin (7) that exhibit conductivity and form a portion of a container for storing fuel, an internal structure (19) formed from a metal, and an inner surface layer (15) which has semiconductor properties or insulating properties and is formed in an integral manner on the inner surfaces of the upper skin (5) and the lower skin (7) in a location where the internal structure (19) contacts the upper skin (5) and the lower skin (7), and in the surrounding portion thereof, wherein the inner surface layer (15) is formed, at least in the surrounding portion, from a material having semiconductor properties.

Abstract: A cap (9) that is used in a fixing structure (1) for fixing a plurality of overlaid structural members (3) by means of a fastener (5) inserted into through-holes (3a) formed in the overlaid structural members and a collar (7) fastened onto a distal end (5a) of the fastener protruding from a surface of the structural members and that is disposed so as to surround the distal end of the fastener and the collar. The cap is attached, in a non-engaged state, to the distal end of the fastener and the collar, and a concave groove (9d) that accommodates a sealant (11) to be filled in a space formed between an inner peripheral surface (9e) and the surface of the structural members is formed in the inner peripheral surface.

Abstract: 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 hole 32 is formed in a cap 30, and a screw groove 32a is formed in the hole 32. The configuration enables the cap 30 to be reliably and easily positioned and installed on a fastener member 24 and reliably prevents the cap 30 from coming off after the installation thereof. This improves the workability to reduce the production cost while assuring sufficient insulation properties and enables the cap 30 to be installed with stable quality irrespective of workers. Preferably, the cap 30 is made of a resin in view of mass producibility, weight reduction, and the like.

Abstract: A fuel gauge (15) provided with a columnar inner structural body (27) that is formed of an insulator; a hollow-cylindrical outer structural body (23) that is formed of an insulator and disposed on the outer circumference side of the inner structural body (27) over the entire circumference thereof and at a distance therefrom; an inner electrode (29) that is attached to an outer circumferential surface of the inner structural body (27); and an outer electrode (25) that is attached to an inner circumferential surface of the outer structural body (23); which measures the capacitance between the inner electrode (29) and the outer electrode (25) and detects the level of fuel that exists between the inner electrode (29) and the outer electrode(25), wherein the outer structural body (23) is provided with a plurality of outer through-holes (31) that allow electric charge to move from an outer circumferential surface thereof to the outer electrode (25).

Abstract: Provided is a coating material that can prevent galvanic corrosion and is resistant to electrostatic charging. An antistatic coating comprising a primer containing either an inorganic fiber comprising Si, Ti or Zr, C, and O, or an Ag filler. Further, a structure made of a composite material which is resistant to galvanic corrosion and electrostatic charging is obtained by applying the antistatic coating containing either an inorganic fiber comprising Si, Ti or Zr, C, and O, or an Ag filler to the surface of the structure made of a composite material to form a layers.

Abstract: A lightning-resistant fastener, a cap, a fastener member, and a method for attaching the lightning-resistant fastener are provided, which enhance workability and quality stability besides reliably securing an insulating property, and can lead to enhancement in safety of an airframe and reduction in manufacturing cost. A head portion 25b of a fastener main body 25 includes a head cap 50, and a shaft portion 25s of the fastener main body 25 includes a shaft cap 30, whereby a direct strike of lightning to a fastener member 24, and occurrence of an arc discharge from the fastener member 24 in the case of a lightning strike can be suppressed. A hole 52 is formed in the head cap 50, and a thread groove 52a is formed in the hole 52, whereby the head cap 50 can be reliably and easily positioned and attached to the fastener member 24.

Abstract: 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.