Abstract: An electric wire protecting device is used in order to be capable of being installed in a narrow wiring area like one in a small aircraft, and to minimize a risk of an electric arc inside electric wire bundles at low costs. To this end, the electric wire protecting device includes: power wire groups each of which is an assembly of one or more power wires at the same potential; a tape for binding the power wire groups at different potentials from one another into one bundle at a constant pitch; and a spacer extending in a direction of extension of the power wire groups, and inserted in boundaries between the power wire groups.
Abstract: An aircraft including: a penetration member that penetrates an airframe between an inside and an outside via an opening provided in the airframe; a seal that seals a gap set between an opening formation member forming the opening and the penetration member; and a retainer that presses the seal against the penetration member and the opening formation member, wherein each of the penetration member and the opening formation member includes a receiving section that receives the seal, both of the receiving sections are arranged along a direction connecting one side and the other side of the gap with the gap therebetween, and the seal is fixed to only one of the receiving section of the penetration member and the receiving section of the opening formation member.
Abstract: An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions (40A, 40B) are formed in a single vent stringer (20), and thus even in a case where one of the opening portions (40A, 40B) is blocked, ventilation is secured by the other opening portion. At this time, since the opening portions (40A, 40B) are formed in surfaces different from each other in the vent stringer (20), a possibility that both the opening portions (40A, 40B) may be simultaneously blocked is less.
Abstract: An antenna cover of an aircraft including: a cover that protects an antenna mounted in the aircraft; a conductive layer having conductivity that is provided on an outer side of the cover; and a rain erosion boot that covers one region of the conductive layer, wherein the rain erosion boot includes a main material having an insulating property, is given conductivity, and is grounded to an airframe via the conductive layer, or the rain erosion boot includes a main material having an insulating property, and is given hydrophilicity.
Abstract: An aircraft comprising a fuselage; a main wing provided on a fuselage lower side and including a center wing and an outer wing; and a fairing covering at least a lower surface of the center wing, and a seal interposed between an end edge in a right-left direction of the fairing and an outer wing lower surface. In the aircraft, a most outboard fitting located on a most outboard side out of fittings respectively provided at a plurality of positions in the right-left direction of the fairing, and an outer wing fitting provided on the outer wing are pin-coupled via a pin or pins extending along a front-rear direction. The outer wing fitting is coupled to the outer wing at a position on an inboard side with respect to the end edge and other than a position of a joining structure for joining the center wing and the outer wing.
Abstract: An electric wire structure keeps down the weight and improves the ease of routing, as well as allows an existing electric wire to be easily provided with measures against electromagnetic waves. The electric wire structure includes: a single or plurality of electric wires; a single or plurality of GND members which are disposed around the electric wires along the electric wires and are grounded at both ends; and a bundling member for directly bundling the electric wires and the GND members which are not covered integrally by a jacket.
Abstract: The present invention provides a water inflow prevention device that prevents an inflow of water into an aircraft when the aircraft lands in water through a communication passage allowing the inside and outside of the aircraft to communicate with each other. The water inflow prevention device includes a mesh part provided in the communication passage, through the mesh part a fluid flowing through the communication passage passes.
Abstract: An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted.
Abstract: Provided is a mandrel which is inserted into a pipe material when the pipe material is bent, the mandrel including: a core member having a rod-shaped main body portion and a small-diameter portion which is provided on one end side of the main body portion and which is thinner than the main body portion; and a front end member which is provided on one end side of the core member and which is formed integrally with the core member so as to cover the small-diameter portion.
Abstract: An aircraft with a turbofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the ignition plug, and at least a part of the igniter cable is passed through an inside of the pylon.
Abstract: A row formed by a plurality of windshield fasteners, which fasten an outboard retainer, a panel, and an inboard retainer of a windshield of an aircraft, along a peripheral edge part of the windshield panel includes a first fastener, which is disposed at a predetermined position, and a pair of second fasteners, which is disposed in alignment with the row, one on each side of the first fastener. A plate, which is fastened along with the windshield panel by the first fastener and the pair of second fasteners, is disposed on the inboard retainer on the inside of the aircraft. The first fastener can be attached to or detached from a fixing nut, which is fixed on the plate, from the outside of the aircraft, and can be replaced with a suspension fastener on which a wire to be mounted on the windshield can be fitted.
Abstract: An aircraft includes: a cockpit, the inside of which is pressurized; equipment which is at least partially disposed on the outside of the cockpit (external space) where the pressure is lower than the inside of the cockpit (internal space); a forced air delivery mechanism which discharges air from a peripheral space of the equipment on the outside of the cockpit by an exhaust fan to supply a branch flow divided from a main flow of air-conditioning exhaust, which has air-conditioned the inside of the cockpit, as cooling air to the equipment; and a natural air delivery mechanism which uses a differential pressure between the inside of the cockpit and the outside of the cockpit to supply air inside the cockpit as cooling air to the equipment through a ventilation opening putting in communication the peripheral space and the inside of the cockpit with one another.
Abstract: A penetrated floating nut includes: a first retaining member including a cylindrical first cylindrical section and a first flange section provided at one end portion of the first cylindrical section; a second retaining member including a cylindrical second cylindrical section and a second flange section provided at one end portion of the second cylindrical section, the second cylindrical section being joined to the first cylindrical section of the first retaining member; and a nut housed in the first cylindrical section of the first retaining member with a gap therebetween and including a third flange section at one end portion of the nut and further including rotation stopping means between the nut and the first cylindrical section of the first retaining member, the third flange section being housed in the second cylindrical section of the second retaining member with a gap therebetween and being capable of contacting an end surface of the first cylindrical section of the first retaining member.
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: There is provided a drainage system of an aircraft which discharges moisture having entered inside horizontal tails, which are structures of an airframe of an aircraft, toward the rear end of a fuselage, the drainage system including: a drainage channel which includes an introduction end and a discharge end, and by a capillary action delivers moisture introduced from the introduction end toward the discharge end; and a heater which heats and dries the moisture delivered through the drainage channel. The drainage channel of the present invention is preferably composed of a paper drainage material. It is also preferable that the introduction end of the drainage channel is provided in a lowermost region in the vertical direction within an area in which moisture can accumulate inside the horizontal tails while the aircraft is parked.
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: To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded.
Abstract: Provided is a fuel system that can reduce the amount of fuel in a second tank before the amount of fuel in a first tank. A fuel system includes: a first tank and a second tank that respectively store fuel; a fuel supply pump that supplies at least the fuel in the first tank out of the first and second tanks to a fuel consuming section; a transfer pump that transfers the fuel in the second tank into the first tank; and a fuel passage having an inlet in communication with an inner portion of the first tank, and an outlet in communication with an inner portion of the second tank. The fuel in the first tank overflows into the second tank through the fuel passage.
Abstract: The present invention provides an aircraft safety device which can reliably prevent explosion of a fuel tank even if an inflammable gas is ignited. A safety device for explosion-proofing a fuel tank which stores fuel of an aircraft includes: a flame propagation blocking part which blocks propagation of a flame from the outside to the inside of the fuel tank through a ventilation passage which allows ventilation between the inside and the outside of the fuel tank; and a gas supply suppressing part which, when heated by the heat of the flame, suppresses supply of an inflammable gas containing the fuel gas to the flame through the ventilation passage.
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.