Abstract: The present invention aims to sufficiently impregnate each layer of a fiber substrate group composed of fiber substrates, which are used for fiber-reinforced resin molding by a resin injection method, with a resin. To successively stack a plurality of fiber substrates, each of which has arrayed fiber bundles and is a material composing a fiber-reinforced resin along with a resin, with their fiber bundles oriented in the same direction, the plurality of fiber substrates are integrated in a state where border zones between the fiber bundles adjacent to each other in an array direction are aligned with one another among the fiber substrates.

Abstract: Under constraints on the space and the weight of an aircraft, the present invention aims to protect structural members from a heat generation part. An aircraft includes: a fuselage; an air conditioning pack installed on the outside of a lower part of the fuselage; a fairing covering the air conditioning pack; an outer heat insulation material disposed in a region of the fuselage, which corresponds to the air conditioning pack, from the outside of the fuselage; and an inner heat insulation material disposed around the region on the inside of the fuselage.

Abstract: A device for determining an electrical wire bundle, in which, when the electrical wire bundle includes even one test electrical wire which conducts electricity to a terminal device, the electrical wire bundle is given an A-rating indicating an electrical wire bundle to be used for a test; when the electrical wire bundle includes at least one electrical wire which conducts electricity to the terminal device but is not the test electrical wire, the electrical wire bundle is given a B-rating indicating that the electrical wire bundle is not allowed to be disconnected; and when the electrical wire bundle includes only electrical wires that do not conduct electricity to the terminal device, the electrical wire bundle is given a C-rating indicating an electrical wire bundle not to be used for the test.

Abstract: The invention deals with the restriction on the mode change of an engine due to latching in the case of restarting the engine that has stopped in flight. A FADEC that controls an engine of an aircraft in accordance with a mode, includes a latch operating section that latches the mode, and an in-parking/in-flight determining section that determines whether the aircraft is on the ground or flying off the ground. The latch operating section operates when the in-parking/in-flight determining section determines the aircraft is on the ground, and does not operate when the in-parking/in-flight determining section determines that the aircraft is in fight.

Abstract: There is provided a panel member capable of restraining an increase in weight of a wing panel while restraining wasteful work in the manufacturing process, an aircraft main wing, and a method for forming the panel member. A wing panel 10 is formed with ridges 20 each having a dimension larger than the machining tolerance in the boundary portions between areas A1, A2, . . . . Therefore, the worker who handles the wing panel 10 can visually confirm the step portions of the areas A1, A2, . . . easily. Thereby, if a flaw or the like is found in the areas A1, A2, . . . , corrective actions can be properly taken on the actually existing flaw without mistaking the flaw for the step portion of the areas A1, A2, . . . .

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: To provide an aircraft strength testing apparatus that, using a curved specimen, can produce a desired stress safely and quickly by reliably applying an internal pressure, and moreover allows any resulting damage to be reliably observed. A testing apparatus 1 that applies an internal pressure, equivalent to a differential pressure between the outside and the inside of a section to be tested of a fuselage of an aircraft, to a curved specimen 10 corresponding to the section to be tested, includes: a pressure vessel 22 between which and the specimen 10 a cavity 23 is formed; and rods 25 that restrain the specimen 10 against the internal pressure. The pressure vessel 22 faces the outer side of the specimen 10. By reducing the pressure inside the cavity 23, an internal pressure is applied to the specimen 10.

Abstract: The present invention provides a method for mounting an aircraft engine, which enables to speed up a mounting work by facilitating positioning of an engine with respect to a pylon. The method for mounting an aircraft engine, including: lifting up an engine of an aircraft toward a pylon that is a mounting object; and when the engine reaches a predetermined position, fixing the engine to the pylon, wherein guides that perform horizontal positioning of the engine with respect to the pylon are respectively provided on a front side and a rear side of the engine.

Abstract: A fire extinguishing system of an aircraft including: a fire extinguishing nozzle that is provided on an installation member forming a compartment of the aircraft; and a fire extinguishing pipe that is provided on a support structure supporting the installation member from a back side, and supplies a fire extinguishing agent to the fire extinguishing nozzle, wherein the fire extinguishing pipe includes a first pipe that is supported by a first support member constituting the support structure, a second pipe that is supported by a second support member constituting the support structure and crossing the first support member, and a tube having flexibility that connects the first pipe and the second pipe.

Abstract: A failure rate calculation device calculates the failure rate of a wire harness of which each of a plurality of electrical wires is connected with connectors via relay points, the device including: a storage unit which stores electrical wire-connector connection information in which each of the plurality of electrical wires and the connectors are associated with each other and in which type information on each of the electrical wires and type information on each of the connectors are associated with each other, and failure rate information in which the type information belonging to the electrical wire-connector connection information and failure rate factors, associated with the type information, are associated with each other; and a processing unit which, when the wire harness is specified, checks the electrical wire-connector connection information and the failure rate information against each other and calculates a failure rate in the wire harness.

Abstract: The present invention provides a windshield device including: a windshield; a heater that is provided in the windshield and configured to generate heat by energization; a temperature sensor that is provided in the windshield and configured to detect a temperature; and a control unit that performs power control on the heater. The control unit is configured to supply an input power to the heater, the input power being acquired by applying a detected temperature detected by the temperature sensor to a function that is determined in accordance with a dew-point temperature of an inside of a compartment separated from an outside of the compartment by the windshield.

Abstract: A computer system 20 provided in an aircraft 1 includes, as a module of a computer program to be executed, an approach determination section 31 configured to determine whether the aircraft 1 is approaching a landing site. The approach determination section 31 includes, as a condition for determination of approaching, establishment (C1) of one or both of a condition (C11) that a first absolute altitude A1 obtained by an radio altimeter 21 mounted on the aircraft 1 is low relative to a first approach altitude AA1, and a condition (C12) that a second absolute altitude A2 that is obtained by subtracting an altitude AL of the landing site from a pressure altitude Ap determined by a barometric altimeter 22 mounted on the aircraft 1 is low relative to a predetermined second approach altitude AA2.

Abstract: The present invention provides a vibration excitation system which allows a vibration exciter to be easily mounted on/removed from a wing. The present invention is a vibration excitation system for an aircraft which imparts vibration to a main wing of an aircraft subjected to a test flight, for evaluation of vibration resistance to flutter. A vibration exciter which generates vibration is removably mounted on the main wing through a fixing structure. It is preferable that the fixing structure transmit the vibration of the vibration exciter as a shearing force to a front spar and a rear spar of the main wing.

Abstract: The present invention aims to sufficiently impregnate each layer of a fiber substrate group composed of fiber substrates, which are used for fiber-reinforced resin molding by a resin injection method, with a resin. To successively stack a plurality of fiber substrates, each of which has arrayed fiber bundles and is a material composing a fiber-reinforced resin along with a resin, with their fiber bundles oriented in the same direction, the plurality of fiber substrates are integrated in a state where border zones between the fiber bundles adjacent to each other in an array direction are aligned with one another among the fiber substrates.

Abstract: The present invention provides an aircraft including: a main wing; and a flight control surface that is deployed from the main wing in a first direction and in a second direction different from the first direction. In the aircraft, an end surface of the flight control surface facing the main wing when the flight control surface is not deployed is inclined with respect to the first direction or the second direction on at least one side of a longitudinal direction of the flight control surface, and a portion of the main wing facing the end surface is also inclined with respect to the first direction or the second direction in accordance with the end surface.

Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a plurality of walls including: a first wall provided on a first partitioning member; and a second wall provided on a second partitioning member. One of the plurality of walls is a spring wall that functions as a spring. The first and the second partitioning members define the fire-prevention region. The plurality of walls forms a labyrinth-shaped gap between the first and the second partitioning members. Each of the plurality of walls contains a refractory material and includes a front end part. When the first and the second partitioning members are stationary with respect to each other, the front end part is not in contact with another member, and the spring wall is disposed closest to a facing member, among the plurality of walls.

Abstract: The present invention aims to apply a vertical load to a specimen with high precision even if the specimen shifts horizontally. A load application device includes: a hydraulic actuator which applies a load to a specimen; a support structural body which supports the hydraulic actuator along a vertical direction; a horizontal guide surface which guides the support structural body along a horizontal direction; and a bearing which is interposed between the support structural body and the horizontal guide surface and bears the support structural body so as to be horizontally shiftable relative to the horizontal guide surface. This bearing includes a plurality of spherical bodies supported so as to be independently rollable, and the plurality of spherical bodies are held in contact with the support structural body or the horizontal guide surface.

Abstract: To provide a structure maintenance supporting system that can accurately and quickly associate any position on a structure with a position in the drawing of the structure that is referred to at the time of maintenance. A maintenance supporting system includes an image displaying device that displays an image of a structure to be referred to when any damaged position on the structure is maintained, and a processing unit that performs calculation to associate the damaged position with a position in the image. The processing unit includes a damaged position calculating section that calculates a target coordinate which is the coordinate of the damaged position using known coordinates given to a plurality of reference points, and a position specifying section that specifies a position in the image corresponding to the target coordinate with an indication on the image displaying device.

Abstract: Provided is a preform member bonding method, in a RTM process, for bonding a preform member and another member (a preform member or a hardened member) together with an adhesive. The preform member bonding method includes: beforehand obtaining data on a range of a level of progress in hardening of the adhesive which allows the adhesive to penetrate the preform member, and data on a range of the level of progress in the hardening of the adhesive which decreases bonding strength of the adhesive; and controlling the level of progress in the hardening of the adhesive by heat-treating the adhesive based on these data, before the preform member comes into contact with the adhesive.

Abstract: A seal structure for sealing a gap between a first member and a second member of an aircraft includes: a plate spring-shaped first elastic seal; and a second elastic seal. When the first member and the second member are stationary with respect to each other, the first elastic seal elastically deforms between the first member and the second member to seal the gap, whereas the second elastic seal does not seal the gap. When the first member and the second member move closer to each other and the first elastic seal is elastically deformed, the second elastic seal elastically deforms between the first member and the second member to seal the gap.