Abstract: To surely grasp an unlocked state of a cowl member while suppressing cost and time necessary for measures against forgetting of locking of an engine nacelle. An aircraft according to the present invention includes: an engine (3) that includes an engine main body (4, 5) outputting thrust force and an engine nacelle (7) surrounding the engine main body (4, 5); an engine pylon (2) that supports the engine main body (4, 5) to a main wing (1) and axially supports a cowl member (8) to be openable, the cowl member (8) configuring the engine nacelle (7); a locking part (30) that locks the cowl member (8) of the engine nacelle (7) in a closed state; and one or more light emitting sections (15) that are disposed inside the cowl member (8) and show an unlocked state of the cowl member (8).
Abstract: To provide a nitrogen enriched air (NEA) supply system which easily maintains low the concentration of oxygen within a tank before fueling. In the present invention, a subsidiary pipe 20b that directly supplies NEA to a spill-back pipe 23 is provided. In a descent phase of an aircraft, the NEA is supplied to a second fuel tank 17 from the subsidiary pipe 20b. When the second fuel tank 17 is fueled after landing, the stored NEA is pushed out into a first fuel tank 15 through the spill-back pipe 23 by fuel F. Thus, the concentration of oxygen within the first fuel tank 15 can be also maintained low. Accordingly, it is possible to cut out the need for supplying the NEA before fueling, and thereby fuel the fuel tank while avoiding fuel explosion.
Abstract: The present invention provides a pipe structure including: a pipe through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere flows; a cover that covers an outer peripheral portion of the pipe, and defines a plurality of vents from which the gaseous body leaking from the pipe flows out; and a line-shaped sensor that passes a position corresponding to each of the plurality of vents, and is sensitive to a temperature or a concentration of the gaseous body outside the cover, wherein the sensor includes a range in which the sensor rises upward from the position corresponding to the vent.
Abstract: There is provided an anti-icing system that has a simple structure and makes it possible to exert anti-icing performance by dealing with displacement of a stagnation point without increasing air resistance. The anti-icing system according to the present invention blows heated gas to an inner surface of a wing of an aircraft, and includes: a piccolo tube that includes a flow path through which the heated gas flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and a supply source that supplies the heated gas toward the piccolo tube. The piccolo tube is held to cause positions of the respective ejection holes to be fixed in a gravity direction.
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: A bundle diameter calculation device calculates the number of electrical wires belonging to an electrical wire bundle constituting a part of a wire harness of which each of the plurality of electrical wires is connected via relay points with connectors, 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 bundle connection information which shows a state of connection with the connectors and relay elements by the unit of the electrical wire bundle of the wire harness; and a processing unit which, when the wire harness is specified, checks the electrical wire-connector connection information and the bundle connection information against each other and calculates the bundle diameter of the electrical wire bundle.
Abstract: An insulative ring protects a burst disc of an aircraft from the shock of lightning strikes. The burst disc device includes: a burst disc which is installed inside a main wing to prevent over-pressurization of the main wing; a pressure release passage partially constituted by a support tube and is blocked with the burst disc and leads to the outside of the main wing; an insulative ring which is disposed along the inner peripheral edge at a terminal end of the pressure release passage and exposed to the outside of the main wing, and an insulation layer which is disposed between a flange of the support tube and an inner surface of a panel of the main wing.
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 reduce a time required for repairing a honeycomb core sandwich panel. A repair method according to the present invention is a repair method, in which a repair patch 20 is disposed on a repair target portion that exists on the side of a repair surface 1A of a honeycomb core sandwich panel 1, the honeycomb core sandwich panel 1 being formed by sandwiching a honeycomb structured core 10 with a plurality of cells between skins 11 and 12, the method including: a heating step of heating the repair patch 20; and a cooling step of cooling the honeycomb core sandwich panel 1 from the side of a second surface 1B opposing the repair surface 1A of the honeycomb core sandwich panel 1.
Abstract: An aircraft window includes: a window body including window panels, and an electromagnetic shield layer laminated on the window panels; a window frame that is made of a conductive material, and that surrounds the window body; a rubber-based gasket provided with conductivity, the gasket being at least partially held between the window body and the window frame; and a conductive layer that is located between the window body and the gasket, and that brings the electromagnetic shield layer and the gasket into conduction with each other. The window frame includes a holding section that holds the window body. At least a part of the conductive layer extends to a portion of the window body facing an extending part of the holding section. Moreover, the conductive layer extends about an entire perimeter of the window body, and extends only partially along an interface between the window body and interposition member.
Abstract: The present invention provides a device which can uniformize heat distribution by using an existing heater mat for repairing or joining members. A heat dispersion device includes a bag with a fluid sealed inside, and is disposed on a second surface of a heater mat which has a first surface to be directed toward an object to be heated and the second surface opposite to the first surface. The fluid inside the bag is preferably heated with a heat source.
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.
November 1, 2017
Date of Patent:
June 11, 2019
MITSUBISHI AIRCRAFT CORPORATION
Koji Toyama, Satoshi Suehiro, Yoshihiro Nakayama
Abstract: An aircraft duct structure includes a first duct through which exhaust air from a front-side equipment compartment flows, and a second duct through which exhaust air from a rear-side equipment compartment flows. The first duct has a terminal end part where the exhaust air inside the second duct flows into the exhaust air inside the first duct at a substantially right angle, and a flow straightening plate located inside the terminal end part. The terminal end part has a jet opening which faces, across a clearance, an air pressure regulating port where an air pressure regulating valve is disposed. The inside of the terminal end part is divided by the flow straightening plate into an upper region and a lower region. The exhaust air inside the first duct and the exhaust air inside the second duct merge together in the upper region.
Abstract: The present invention provides a pipe structure including: a pipe through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere flows; a cover that covers an outer peripheral portion of the pipe, and defines a plurality of vents from which the gaseous body leaking from the pipe flows out; and a guide member that guides the gaseous body flowing out from the vent toward a line-shaped sensor that passes a position corresponding to each of the plurality of vents, and is sensitive to a temperature or a concentration of a gaseous body outside the cover.
Abstract: There is provided a safety device for aircraft, that prevents an explosion of a fuel tank storing aviation fuel, the safety device including: a flame arrester that is arranged near an end of a ventilation passage on an aircraft outer side, as a part of the ventilation passage allowing the inside of the fuel tank and an outside of the aircraft to communicate with each other, to prevent a flame propagation into the fuel tank from the outside of the aircraft through the ventilation passage; and a heat transfer reducing part that is arranged closer to the outside of the aircraft than the flame arrester to prevent heat transfer to the fuel in the fuel tank from the flame.
Abstract: The present invention provides a method for locating a machining position in a repair material that is arranged on a member including a machined portion formed by predetermined machining, the method including: a step of arranging a marker including a portion having a different propagation characteristic of an ultrasonic wave from that of a peripheral portion in the machined portion existing in the member before the repair material is arranged on the member; and a step of applying the ultrasonic wave to the member covered with the repair material and locating the machining position at a position of the marker captured by the ultrasonic wave after the repair material is arranged on the member.
Abstract: A fire extinguishing system of an aircraft including a nozzle device that is provided on an installation member forming a compartment of the aircraft, wherein the nozzle device includes: a nozzle that is passed into an insertion hole formed in a nozzle installation section provided on the installation member, and discharges a fire extinguishing agent supplied from a supply source into the aircraft compartment; and a lid member that closes a gap between the nozzle and the nozzle installation section.
Abstract: The method of forming reinforced fiber base material is provided with: arranging, on the mold having a projection with a upper surface, a platform that is adjacent to the projection and has a flat upper surface at the same height as the upper surface of the projection; forming the laminate by placing reinforced fiber base material in layers on the upper surface of the projection; placing an end of the laminate in the width direction extending out of the upper surface of the projection, on the upper surface of the platform, with the end of the laminate in the width direction sandwiched in a vertical direction by a pair of the films of which outer ends in the width direction are fixed to each other; and removing the platform and pulling out the pair of the films while shaping the laminate along the projection.
Abstract: The present invention has an objective to provide a leading-edge structure for an aircraft that is capable of, in the case of a collision with an airborne object, effectively absorbing the energy of the collision with the airborne object, with no increase in its weight. A leading-edge structure (10) for an aircraft according to the present invention includes a spar (11) extending in a predetermined direction, a plurality of ribs (13) provided in the predetermined direction of the spar (11) at intervals, and a skin (17) supported by the plurality of ribs (13). The ribs (13) includes first ribs 14 and a plurality of second ribs 15 that are disposed between the pair of first ribs (14). The second ribs (15) do not support the skin in the vicinity of their front ends.