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: To provide a negative electrode material having a high initial capacity and a long charge and discharge cycle life A negative electrode material according to the present invention contains a particle of a negative electrode active material that occludes and releases lithium ions and a carbon fiber, wherein the negative electrode active material occludes lithium by forming an alloy with the lithium, a surface of the negative electrode active material particle is coated with carbon, and the carbon fiber is bonded to the surface of the carbon via an adhesive resin.

Abstract: In order to simplify the equipment for heating a thermosetting resin or a thermoplastic resin and to reduce manufacturing costs of a molded resin article by saving energy, this resin composite material (1A-1I) is formed by combining a fibrous reinforcing material (2) and a thermosetting or thermoplastic matrix resin (3), wherein a metal nanomaterial (4) which self-heats after absorbing electromagnetic waves is added to the matrix resin (3). The frequency of the electromagnetic waves is preferably within the range of 3 MHz to 3 GHz. The metal nanomaterial (4) is preferably nanofibers or nanocoils, and the material is preferably platinum or gold.

Abstract: Provided is a method of manufacturing a structure, the method including: a molding step of impregnating the carbon fibers with the resin material and curing the resin material for molding a carbon fiber composite material; a polishing step of polishing a polishing region on a surface of the carbon fiber composite material molded in the molding step, with an abrasive that has a predetermined hardness; and a bonding step of bonding, through an adhesive, another member to a part of the polishing region polished by the polishing step. The molding step forms, in a top layer, a polishing layer that has hardness lower than the predetermined hardness, and forms a surface protective layer that is lower than the polishing layer, protects the carbon fiber composite material from the abrasive, and contains a protective filler having hardness higher than the predetermined hardness.

Abstract: Provided is a structure manufacturing device (100) including a constant-current power supply (10) that is configured to apply a current having a predetermined current value to a gap that is present between a composite material (31) and a bolt (32), each having conductivity, and has a higher electrical resistance than the composite material (31) and the bolt (32) in order to decrease the electrical resistance of the gap.

Abstract: A curing device of a resin composite material is provided with: an environment setting unit (an electromagnetic wave irradiation unit) which applies a prescribed physical environment that increases the amount of momentum of the molecules in an object (for example, irradiation by electromagnetic waves) to an uncured resin composite material which contains a metal nanomaterial that self-heats when placed in the aforementioned specific physical environment (the electromagnetic waves); a pressing body which is provided so as to be capable of pressing against the surface of the resin composite material; and a pressing driving unit which presses the pressing body against the surface of the resin composite material in a state in which the environment setting unit (the electromagnetic wave irradiation unit) is applying the aforementioned specific physical environment (for example, irradiation by electromagnetic waves) to the resin composite material.

Abstract: The purpose of the present invention is to provide a bonded structure, a method for manufacturing the same, and a bonding state detection method which are capable of determining whether or not members are bonded together appropriately. A bonded structure 10 includes a laminated sheet 12A, a laminated sheet 12B, an adhesive 14 that bonds the laminated sheet 12A and the laminated sheet 12B together, and a distributed optical fiber 16 sandwiched between the laminated sheet 12A and the laminated sheet 12B. The cross-sectional shape of the distributed optical fiber 16 is deformed in accordance with the bonding state.

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: This structure is provided with a first composite material 11, a second composite material 12 joined to the first composite material 11 by a film adhesive 21 provided between the first composite material 11 and the second composite material 12, and a corner fillet part 13 provided on a corner part 15 formed by the first composite material 11 and the second composite material 12. The shape of the corner fillet part 13 is a design shape P designed in advance, and the corner fillet part 13 is formed by curing the film adhesive 21 after arranging the film adhesive 21 on the corner part 15 so as to fit into the design shape P.

Abstract: A composite structure includes a first composite material, a second composite material bonded to the first composite material, and a corner fillet part provided at a corner part formed by the first composite material and the second composite material. In the composite structure, the rigidity of the corner fillet part is adjustable, and a pull-off stress to be applied to the corner part is adjusted by adjusting the rigidity of the corner fillet part. The pull-off stress to be applied to the corner part is adjusted to be decreased by adjusting the rigidity of the corner fillet part to be decreased.

Abstract: This composite material structure is provided with: a first composite member arranged facing a heating element, the first composite member including PAN-based carbon fibers; a second composite member arranged between the heating element and the first composite member, the second composite member including pitch-based carbon fibers; and a cushioning element provided between the first composite member and the second composite member, the cushioning element being joined to each of the first composite member and the second composite member, and having lower rigidity than those of the first composite member and the second composite member. The first composite member is provided so as to be linked to an adjacent structure, while the second composite member and the cushioning element are provided so as to be separated from the structure.

Abstract: The purpose of the present invention is to provide a lightweight composite material structure while suppressing a drop in strength. In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes (5) formed at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region (3a) around the holes (5) comprises a first area (10) obtained by bending composite material, which is reinforced using continuous fibers that have been made even in the longitudinal direction, so that the center line of the width (W) of the composite material weaves between adjacent holes (5) and zigzags in the one direction.

Abstract: A composite material structure is composed of a first face plate and a corrugated core bonded to the first face plate. The corrugated core has at least one opening.

Abstract: An FRP shaping jig has a main structure holding jig (22) and a reinforcement part holding jig (26A; 26D) with flexibility. The FRP shaping jig is used when a main structure (12) and a reinforcement part (14A; 14B) are joined to shape an FRP structure 10. The main structure holding jig (22) positions and holds the main structure (12) configured from a fiber component. The reinforcement part holding jig (26A; 26D) is positioned to the main structure holding jig (22) and positions and holds the reinforcement part (14A; 14B) while pushing the reinforcement part (14A; 14B) configured from a fiber component.

Abstract: A core (20) and a bag (22, 24) are provided which are used to shape an FRP structure (10; 30). The bag (22, 24) has a core bag section (24) which covers the outer circumference of the core (20), and a coverture bag section (22) which covers a plurality of fiber components (12, 14; 12, 14, 16).

Abstract: A composite structure (3) formed of a composite member which extends in one direction, includes holes (5), and is made of fiber reinforced plastics. A tensile load and/or a compressive load are applied to the composite structure (3) in the one direction. Tensile stiffness and/or compression stiffness of peripheral areas (3a) of the holes (5) is lower than tensile stiffness and/or compression stiffness of the other area (3b), which surrounds the peripheral areas (3a), in the one direction, and the width of the peripheral area (3a) in a direction orthogonal to the one direction is set to 1.1 times or less of the diameter of the hole (5) in the direction orthogonal to the one direction.

Abstract: To provide a negative electrode material having a high initial capacity and a long charge and discharge cycle life A negative electrode material according to the present invention contains a particle of a negative electrode active material that occludes and releases lithium ions and a carbon fiber, wherein the negative electrode active material occludes lithium by forming an alloy with the lithium, a surface of the negative electrode active material particle is coated with carbon, and the carbon fiber is bonded to the surface of the carbon via an adhesive resin.

Abstract: Provided is a joint and an aircraft structure wherein it is possible to position a member relative to a preform with high accuracy. A groove into which a plate member (30) is inserted is formed in a pi-shaped joint (20) provided on the preform (21), and the preform (21) and the plate member (30) are connected by being bonded. Moreover, a fitting shape (32A-1) into which the plate member (30) is fitted is formed on the pi-shaped joint (20) on the whole groove bottom face. Additionally, a fitting shape (32A-2) into which the plate member (30) is fitted is formed on a portion of the groove bottom face. Furthermore, fitting shapes (32B-1, 32B-2), into which the groove bottom face that is formed on the pi-shaped joint (20) is fitted, are formed on the surface of the plate material (30) that is fitted with the pi-shaped joint (20).

Abstract: Provided are a lithium secondary battery having improved initial capacity and excellent cycle property, an electrolyte solution for the lithium secondary battery, and an additive for the electrolyte solution for the lithium secondary battery. The lithium secondary battery includes positive and negative electrodes both having a lithium-ion intercalation/de-intercalation ability, and a non-aqueous electrolyte solution contacted with the positive and negative electrodes. The non-aqueous electrolyte solution contains lithium hexafluorophosphate and a boroxine compound represented by (RO)3(BO)3 liquefying at 25° C. R(s) each independently represent an organic group of a linear chain alkyl group having 3 or more carbon atoms. Herein, the chain alkyl group may have a branch, and when the branch is included, the number of carbon atoms of the chain alkyl group constructing a linear portion thereof is 3 or more.

Abstract: A joint (20) joins a plate member (26) with a preform (22), wherein an inclined part (28), which is inclined relative to a surface that is orthogonal to the direction in which a tensile load is applied to the plate member (26), is formed on a surface (25) that joins with the preform (22). Moreover, an indented part (38) corresponding to the shape of the inclined part (28) is formed on the preform (22) so that the inclined part (28) of the joint (20) is embedded into the indented part (38). The joint (20) is embedded in and bonded to the preform (22). As a consequence, the strength of the bonding surface of the joint (20) and the preform (22) becomes greater.