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: 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: 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: 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 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: A fastener, of which severe strength is demanded and which can also be applied to a location, in which a flush surface equipment is taken into consideration, and which can be manufactured readily and quickly and reduced in manufacturing cost, is provided. A fastener (1) joins a skin of an airplane and a structural material positioned inside the skin and one end surface of a flush head (3) is covered by an insulator layer (5).

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: 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: 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 HF frequency tuning device includes a resonance cavity in which an HF is introduced, a phase detecting section which generates a sign data representing a sign of a phase difference between a traveling wave and a reflected wave included in the HF in the resonance cavity. The frequency of the HF is repeatedly shifted by a first pitch. The direction of the shift is determined by the sign data for reducing the phase difference. When the sign is inverted, the frequency of the HF is repeatedly shifted to the opposite direction by a second pitch smaller than the first pitch until the sign is inverted again. By this tuning process, the fine tuning of HF can by achieved in a short time.

Abstract: A radiotherapy apparatus includes an acceleration unit configured to generate a charged particle beam. A target is configured to generate a radiation when the charged particle beam is irradiated to the target. A sensor is configured to measure an electric current flowing through the target. A dosimeter is configured to measure a dose of the radiation. A control unit is configured to control the acceleration unit based on the measured electric current and the measured dose.

Abstract: Provided is a lightning-protection fastener that is capable of reliably preventing peeling off of an insulation layer during the operation of an aircraft and of 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 an aircraft assembly equipped with a lightning protection structure that is not easily destroyed by lightning current and that is highly reliable. In an aircraft assembly including a skin (10) in which a CFRP layer (12) serves as a main structure; a shear-tie (11) that support the skin (10) from the inside; and a fastener (1) that couples the skin (10) and the shear-tie (11), a copper foil (13) and an outside GRFP layer (14) are provided on an outer surface side of the skin (10), in this order towards the outside, and a copper paint layer (19), which contains copper powder, is provided on the outside GFRP layer (14).

Abstract: There is provided a fastener able to prevent damage due to environmental factors such as ultraviolet rays, and impact from sanddust, lumps of ice, and raindrops without obstructing a flow of electric shock current that flows along a top surface of an outer skin. The fastener connects an outer skin of an aircraft to a structural member positioned inside this outer skin, and is provided with a dielectric layer arranged to cover one end surface of a head section, and a conductive layer arranged to cover one end surface of this dielectric layer.

Abstract: A transmission type dosimeter includes electrodes configured to collect charged particles ionized with radiation, a body, in a cavity of which, the electrodes are arranged, and a lid configured to seal the cavity in the body. The lid includes a fixing frame section fixed on the body, and a transmission section formed with the fixing frame section as a unit body. The transmission section is thinner than the fixing frame section.

Abstract: A radiotherapy apparatus includes an acceleration unit configured to generate a charged particle beam. A target is configured to generate a radiation when the charged particle beam is irradiated to the target. A sensor is configured to measure an electric current flowing through the target. A dosimeter is configured to measure a dose of the radiation. A control unit is configured to control the acceleration unit based on the measured electric current and the measured dose.

Abstract: A fastener, of which severe strength is demanded and which can also be applied to a location, in which a flush surface equipment is taken into consideration, and which can be manufactured readily and quickly and reduced in manufacturing cost, is provided. A fastener (1) joins a skin of an airplane and a structural material positioned inside the skin and one end surface of a flush head (3) is covered by an insulator layer (5).

Abstract: An HF frequency tuning device includes a resonance cavity in which an HF is introduced, a phase detecting section which generates a sign data representing a sign of a phase difference between a traveling wave and a reflected wave included in the HF in the resonance cavity. The frequency of the HF is repeatedly shifted by a first pitch. The direction of the shift is determined by the sign data for reducing the phase difference. When the sign is inverted, the frequency of the HF is repeatedly shifted to the opposite direction by a second pitch smaller than the first pitch until the sign is inverted again. By this tuning process, the fine tuning of HF can by achieved in a short time.

Abstract: There is provided a fastener able to prevent damage due to environmental factors such as ultraviolet rays, and impact from sanddust, lumps of ice, and raindrops without obstructing a flow of electric shock current that flows along a top surface of an outer skin. The fastener connects an outer skin of an aircraft to a structural member positioned inside this outer skin, and is provided with a dielectric layer arranged to cover one end surface of a head section, and a conductive layer arranged to cover one end surface of this dielectric layer.

Abstract: A radiation treatment apparatus includes a guide and a support member. The guide moves a radiation generating unit along an orbit with a predetermined radius such that an X-ray emitted from the radiation generating unit may cross an isocenter. The support member rotates the guide about a turning axis passing through the isocenter. The radiation generating unit is moved along a spherical plane by the guide and the support member and applies the X-ray toward the isocenter in multiple directions.