Abstract: A method for determining a wiring risk is a method for determining a first risk that electric wires connected to a plurality of terminal devices are bundled into a single harness, and a second risk that harnesses fail at the same time, wherein the first risk is determined by identifying the number of connectors to which a target harness identified from the plurality of harnesses is indirectly connected, and the second risk is determined by matching location information of the target harness to an influenced area by a hazard source, and identifying whether the target harness passes through the influenced area.
September 20, 2013
Date of Patent:
April 2, 2019
MITSUBISHI AIRCRAFT CORPORATION
Koji Toyama, Satoshi Suehiro, Yoshihiro Nakayama
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 fire extinguishing system of an aircraft, including: a fire extinguishing nozzle device 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 device. The fire extinguishing pipe is restrained to the support structure at a plurality of restraint positions. A holding device that holds the fire extinguishing pipe and is provided on the support structure is used at at least one of the plurality of restraint positions. The holding device includes a holding section that holds an outer periphery of the fire extinguishing pipe, and a disengaging section that enables disengagement of the fire extinguishing pipe.
Abstract: The present invention provides a method for repairing a lightning protection material that is made of a metal material and is provided along a surface of a member formed by using a fiber reinforced resin includes: bonding a repair material made of a metal material over a lost region of the member where the lightning protection material is lost by using a liquid adhesive and a sheet-shaped holder that contains and holds the adhesive and is arranged at the lost region.
Abstract: An actuator device includes a first and second actuators. The actuator device comprises a control system that is configured to switch the first actuator to a standby state and switch the second actuator to an active state in response to a first condition set wherein a hydraulic value in a first hydraulic system is equal to or less than a predetermined first threshold value and a second hydraulic value in a second hydraulic system is equal to or more than the predetermined second threshold value; and in response to a second condition set wherein the first hydraulic value is equal to or less than the predetermined first threshold value, the second hydraulic value is less than the predetermined second threshold value, and a difference between a current position and target position of a cylinder of the first actuator is equal to or more than a predetermined third threshold value.
Abstract: The present invention provides a pipe structure including a pipe that is disposed along an approximately horizontal direction, and has a plurality of ducts through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere continuously flows, and a plurality of couplings each connecting the ducts together; and a cover covering an outer periphery of the pipe. The cover defines a plurality of vents from which the gaseous body leaking from the pipe flows out of the cover at an interval in a length direction of the pipe. As the plurality of vents, the cover includes at least first vents located corresponding to the couplings. Respective positions of the first vents are substantially set within a range from a two o'clock position to a ten o'clock position through a six o'clock position in a cross sectional surface of the cover.
Abstract: The present invention provides a wire harness manufacturing support system including: a worktable on which a plurality of electric wires constituting a wire harness are wired; and a database that holds wiring route data corresponding to each wire of the plurality of electric wires. The wire harness manufacturing support system is configured so that wiring routes are sequentially displayed on the worktable based on the plurality of wiring route data held in the database.
December 22, 2015
Date of Patent:
December 18, 2018
MITSUBISHI AIRCRAFT CORPORATION
Koji Toyama, Hitoshi Kurahashi, Yoshifumi Ikeda
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: 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: 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: 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.