Abstract: The present invention prevents misassembly of access doors while reducing stress concentrations. A hole-side convex portion 80 is formed in each opening 12 at one or more locations in a circumferential direction, and a door-side rib 70 is formed on each door body 30. The hole-side convex portions 80 formed in the openings 12A to 12C differ in location in the circumferential direction among the plural openings 12A to 12C. The door-side ribs 70 formed on the respective door bodies 30A to 30C are provided in such locations as not to interfere with the hole-side convex portions 80 provided in the openings 12A to 12C in correct combination with the door bodies 30A to 30C.

Abstract: The present invention has an object to provide a lightning current detection sensor that has a configuration resistant to high voltage and high current in a lightning strike and has high sensitivity and high resolution. In a lightning current detection sensor 10, an insulation-coated wire 22 wound in multiple turns is collectively covered with a base tape 21 and a cover tape 23. Thus, even when the insulation-coated wire 22 is wound in multiple turns to increase sensitivity, a minute area can be detected to increase resolution. Also, with the base tape 21 and the cover tape 23 covering the insulation-coated wire 22 and also a shield portion 12 made of an insulating material and a gap 40 formed between the shield portion 12 and the coil portion 20, a sufficient shielding property is ensured and detection with high accuracy can be performed against high current and high voltage without capacitative coupling.

Abstract: An aircraft of the present invention includes an outer panel 4 made of a fiber reinforced plastic material, a support member 5, and a lightning protection fastener 1. The fastener 1 includes a metal fastener body 2 having a shaft portion 10 and a head portion 20, and an insulating member 30 made of an insulating plastic material and mounted to the head portion 20. The portion 20 has a frustoconical-shaped fastener seat surface 211. The panel 4 includes a receiving surface 41 conforming to the fastener seat surface 211. The member 30 includes an insulating seat surface 321 retracted from a plane of the fastener seat surface 211 such that, when a portion 41A of the receiving surface 41 which is opposed to the fastener seat surface 211 is depressed, an insulating seat surface 321 comes into contact with the receiving surface 41.

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 narrow prepreg sheet 20N is bonded along a ridge C, and wide prepreg sheet 20W is bonded to other portions, whereby the wide prepreg sheet 20W having no cut line is bonded to both side portions of the ridge C. In a portion in which a spar 10 is curved, the narrow prepreg sheet 20N is bonded in an axial direction of the spar 10 while divided into plural pieces, and a length of the narrow prepreg sheet 20N is adjusted according to a radius of curvature of the curved portion in the axial direction of the spar 10, whereby various radii of curvature are easily dealt with.

Abstract: To provide an aircraft pylon capable of being mounted to a wing without exertion of preload while ensuring that redundancy is provided in the pylon. An aircraft pylon 50 includes: a pylon strut 11 for supporting an engine of an aircraft; a pin joint mechanism for connecting the pylon strut 11 to a main wing of the aircraft; a link member 15 disposed between the pylon strut 11 and the main wing of the aircraft, wherein the link member 15 includes a collection of plural independent link elements.

Abstract: In order to provide a firewall that is capable of preventing flame passage through a through-hole without any sealant in a connecting part of a component in which a fastener through-hole is formed, a firewall 50 is provided which can prevent a flame from leaking out of the connecting part which connects a first member 51 to a second member 55, particularly through the fastener through-hole TH defined therein. In the firewall 50, the connecting part is a part of a fire-protection chamber 52. As sealing pieces 51d and 51e which also constitute a part of the fire-protection chamber 52 are in contact with each other, the flame is unable to enter into a closed space CA. Thus, the flame would not reach the connecting part, thereby preventing the flame from leaking out of the firewall 50 to the outside of a nacelle 23.

Abstract: A device 100 for molding a fiber-reinforced plastic structure is a device for manufacturing a fiber-reinforced plastic structure 200 integrating a stringer 2, which is a fiber-reinforced plastic member having a longer dimension in a longitudinal direction D than in a direction perpendicular to the longitudinal direction D, with a skin 1, which is a fiber-reinforced plastic member. The skin 1 is provided with a positioning plate 3, which is disposed along the skin 1 and engages with a bottom surface 201 of an end part 21 of a mandrel 20 for molding the stringer 2. The positioning plate 3 positions the stringer 2 relative to the skin 1, at least in the direction intersecting the longitudinal direction D.

Abstract: A method for molding a fiber-reinforced plastic member involves disposing a reinforced-fiber base material 2 inside a molding space S, which is created between a mold 1 and a bag film 6, and then depressurizing the inside of the molding space S and curing a resin composition R contained in the reinforced-fiber base material 2, wherein a flat pressure plate 5 made of spring steel is disposed between the reinforced-fiber base material 2 and the bag film 6. The pressure plate 5 elastically deforms along the shape of the reinforced-fiber base material 2 while the inside of the molding space S is being depressurized, and returns to its original flat shape when depressurization is stopped and the bag film 6 is removed after curing of the resin composition R.

Abstract: In the manufacturing method of the present invention, as preparation for providing a mold 30 with protrusions 31 and 32 to be printed on an FRP material of a skin 1 in co-bold molding, which requires resetting of the skin 1 to the mold 30, a long protrusion 32A and a short protrusion 32B are interchangeable as one protrusion 32. The long protrusion 32A is printed to form a second recessed part 12 in the skin 1, and before the skin 1 is reset, the long protrusion 32A is replaced with the short protrusion 32B. In this way, as the short protrusion 32B is housed in the second recessed part 12 formed during elongation of the mold 30, the skin 1 can be reset in the state of being positioned relative to the mold 30 by the first protrusion 31 and the short protrusion 32B.

Abstract: The molding method of the present invention configures: a mandrel 2 being a mold for molding the material of a fiber-reinforced plastic 1 and having multiple pieces 21 to 24 adjacent to one another in a longitudinal direction D; and an angle material 3 formed of a material having a linear expansion coefficient approximate to the linear expansion coefficient of the fiber-reinforced plastic, and aligning the pieces 21 to 24 along the longitudinal direction D. The method includes: a mandrel disposing step S2 of disposing the pieces 21 to 24 with gaps G1 to G3 between one another; an angle material disposing step S3 of disposing the angle material 3 on the pieces 21 to 24; and a heating to cure and molding step S5 of molding the fiber-reinforced plastic by heating the material of the fiber-reinforced plastic while aligning the pieces 21 to 24 by the angle material 3.

Abstract: An aircraft door 18 which closes an opening of a storage space 16 for storing a RAT 13 as an accessory and which is opened in association with deployment of the RAT 13 from the storage space 16, the door including: a door body 20 that opens and closes the opening, and whose front surface faces an outside and whose rear surface faces the storage space 16 in a closed state; and a fence 24 that rises from the rear surface of the door body 20. In a traveling direction of the aircraft, the fence 24 is located anterior to a position where the RAT 13 is stored. The fence 24 prevents an airflow Air from passing through between the RAT 13 and the door body 20 in an initial stage where the door 18 starts to be opened, thereby suppressing the aerodynamic force in the closing direction acting on the door body 20.

Abstract: To provide a lightning-resistant fastener capable of assuring a sufficient lightning-resistant performance. A cap 30A has an elastically deformable part 50 continuous in the circumferential direction thereof. The elastically deformable part 50 has a smaller thickness than the other parts of the cap 30A in a circumferentially continuous area thereof. Since the cap 30A has the elastically deformable part 50, even if a surface 22b of a member 22 is inclined with respect to a plane perpendicular to the axis of a fastener main body 25, the cap 30A can be installed without forming a gap.

Abstract: The present invention provides an actuator device which can prevent a rapid change in deflection angle when an active actuator and a standby actuator are switched. A first actuator 21A drives an aileron upon supply of hydraulic oil through a hydraulic system 31L from a hydraulic power source 35L. A second actuator 21B drives the aileron upon supply of hydraulic oil through a hydraulic system 31C from a hydraulic power source 35C. In normal cruising, the actuator 21A functions in an active state, and the actuator 21B functions in a standby state. When a hydraulic pressure PA of the hydraulic oil in the system 31L is equal to or less than a predetermined first threshold value PL in the above states, the actuator 21A is switched from the active state to a standby state, and the actuator 21B is switched from the standby state to an active state.

Abstract: A repair method according to the present invention is a method for repairing a honeycomb core sandwich panel 1, the method including: a repair patch disposing step S1 of disposing a repair patch 20 and an adhesive 21A on at least one of a first surface 1A and a second surface 1B of the panel 1, the first outer skin 11 being located on the first surface 1A, and the second outer skin 12 being located on the second surface 1B; a panel restraining step S3 of sandwiching the panel 1 and the repair patch 20 from both surface sides of the first surface 1A and the second surface 1B and thereby restraining the panel 1; and a heating step (thermal curing step) S4 of heating the adhesive 21A while the panel 1 is restrained.

Abstract: A method for repairing a honeycomb core sandwich structural body according to the present invention is a method in which a damaged portion that is formed in a honeycomb core sandwich structural body where a honeycomb structured core is held between a first outer skin and a second outer skin and that reaches the core through the first outer skin is repaired, the method including: a repair material mounting step of mounting a repair material on the damaged portion, the repair material including a patch that covers an opening of the damaged portion, and one or a plurality of braces that support the patch; a patch bonding step of bonding the patch to the first outer skin; and a brace bonding step of bonding the brace to the second outer skin or the core.

Abstract: 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 portion 23 formed in an outer panel 2 with a repairing patch 30, and bond the repairing patch 30 to a repair target, repairing plates 31, 32 that are formed of fibers and thermosetting resin, and pre-cured before repairing are used as the repairing patch 30, and a laminating step S4 of laminating the repairing plates 31, 32, and a bonding step S7 of bonding the repairing plates 31, 32 to each other are performed.

Abstract: 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 portion 14 existing in an outer panel 1, includes: a repairing material disposing step of disposing a repairing patch 21 including a resistance heating element 23 and a carbon fiber reinforced resin, and an adhesive 22A including a thermosetting resin before being hardened for bonding the repairing patch 21 on the repair target portion 14; and a heating-hardening step of heating and hardening the thermosetting resin of the adhesive 22A by causing the resistance heating element 23 to generate heat through supply of electricity thereto.

Abstract: A safety analysis system for wiring, including: a storage unit that stores electric wire-terminal connector correlation information in which each of a plurality of electric wires and a pair of connectors are correlated with each other, terminal connector-function correlation information in which the pair of connectors located at terminals and a function of a device to which the connectors are connected are correlated with each other, and function determination information including a combination of a plurality of functions that are not allowed to be lost at the same time; and a processing unit that matches the electric wire-terminal connector correlation information and the terminal connector-function correlation information when the wire harness is identified, and generates electric wire-function correlation information in which each of the plurality of electric wires and the function of the device are correlated with each other.