Patents Assigned to Mitsubishi Aircraft Corporation
  • Patent number: 10808620
    Abstract: An aircraft includes an accessory member that constitutes an engine accessory, the accessory member being arranged between an aircraft engine pylon and an engine, in an attached state to an attachment base member that is at least one of the pylon and the engine. The accessory member includes: a surrounding portion that surrounds at least an end portion of a tubular body connected to the accessory member; and a projecting portion that projects from the end portion of the tubular body. The entire accessory member including the surrounding portion and the projecting portion is divided so as to be separable to a left side and a right side of the pylon, and the accessory member is attachable to and detachable from the attachment base member by accessing an outer periphery of the tubular body from the left side and the right side of the pylon without removing another member.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: October 20, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Jingo Tateiwa
  • Patent number: 10760489
    Abstract: An aircraft including a turbofan engine provided with an engine body and a fan located anterior to the engine body, further includes: an engine oil cooler that is a heat exchanger for cooling engine oil used in the engine body by using, as a heat source, a fan stream flowing from the fan into a gap between a core cowl surrounding the engine body and a nacelle surrounding the fan and the core cowl; and a pre-cooler that is a heat exchanger for cooling bleed air from the engine body by using the fan stream as a heat source, wherein the engine oil cooler and the pre-cooler are longitudinally arranged in one position in a circumferential direction of the nacelle, and the engine oil cooler is located anterior to the pre-cooler.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: September 1, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Jingo Tateiwa
  • Publication number: 20200269986
    Abstract: To provide an air conditioning piping structure for an aircraft which can promote mixing of temperature adjusted air and recirculated air flowing into a mixing chamber forming an air conditioning system. An air conditioning piping structure causes temperature adjusted air obtained by an air conditioning apparatus of an aircraft and recirculated air discharged from a pressurized compartment to flow into a mixing chamber which mixes the temperature adjusted air and the recirculated air. This air conditioning piping structure includes a first pipe through which the temperature adjusted air flows, a second pipe through which the recirculated air flows, and which is connected to the first pipe, and a flow passage restricting part configured to apply a resistance to at least one of the temperature adjusted air and the recirculated air in a vicinity of a merging position where the temperature adjusted air and the recirculated air are merged.
    Type: Application
    Filed: February 19, 2020
    Publication date: August 27, 2020
    Applicant: Mitsubishi Aircraft Corporation
    Inventors: Takashi Ishimaru, Yasunari Tanaka, Satoshi Hirotsu
  • Publication number: 20200231287
    Abstract: An air-conditioning duct structure of an aircraft includes an air-conditioning duct that is provided on each of a starboard side and a port side and guides conditioned air to a vicinity of a ceiling of a cabin in the aircraft. The air-conditioning duct includes a blowout portion and a blowout upstream portion. The blowout portion blows out the conditioned air to the cabin from an outboard side of the ceiling to an inboard side of the ceiling and toward a lower part than the ceiling, and the blowout upstream portion communicates with an upstream side of the blowout portion. In addition, the blowout portion or the blowout upstream portion is curved to cause a terminal end side of the blowout portion to be inclined downward with respect to a horizontal direction.
    Type: Application
    Filed: December 18, 2019
    Publication date: July 23, 2020
    Applicant: Mitsubishi Aircraft Corporation
    Inventors: Satoshi Hirotsu, Takashi Ishimaru, Yuichiro Shimura, Yasunari Tanaka, Fumio Kondo
  • Patent number: 10718269
    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.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: July 21, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10717243
    Abstract: Provided is a preform member bonding method of bonding a preform member and another member with an adhesive in an RTM process. The preform member bonding method includes increasing viscosity of the adhesive by heat-treating only the adhesive in advance before inserting the adhesive between bonding surfaces of the preform member and the other member.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: July 21, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yuichi Yui, Akihisa Okuda, Hiromichi Akiyama
  • Patent number: 10690058
    Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a first seal compressed and elastically deformed between two members of the aircraft; and a second seal pressed against the first seal in a direction intersecting a compression direction in which the first seal is compressed. A wall of the first seal pressed by the second seal includes a bent groove including at least one bent part.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: June 23, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10661888
    Abstract: The present invention has an objective to provide a dolly for handling a landing gear of an aircraft that enables, while being downsized, work of positioning the landing gear with respect to an attachment portion of an airframe of the aircraft to be performed efficiently, and a method for attaching or detaching a landing gear using the dolly. A dolly (10) for handling a landing gear (20) of an aircraft includes a base (11), an expandable boom (12) that rises from the base (11) and is expandable and contractible, a hoisting boom (13) that is interconnected to the expandable boom (12) in a raisable and lowerable manner, and a holding portion (15) that is suspended on the hoisting boom (13) and retains the landing gear (20).
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: May 26, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yuka Sobajima, Hideyuki Iwata
  • Patent number: 10648408
    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.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: May 12, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10618229
    Abstract: In a molding method using a VaRTM process in which a workpiece is impregnated with resin in a vacuum, the flow channel resistance or the thickness of which is not constant, an air-permeable sheet only permeable to gas and not permeable to resin (liquid) is arranged at the bottom surface of the workpiece to cover the total length of the workpiece in a direction in which the flow channel resistance or the thickness of the workpiece varies, to impregnate the resin.
    Type: Grant
    Filed: April 26, 2016
    Date of Patent: April 14, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yuichi Yui, Hiroshi Tokutomi
  • Patent number: 10611461
    Abstract: A flap of an aircraft includes a flap body that is provided deployably with respect to a main wing, an inclined portion that protrudes from an upper surface of a tip part on at least an outboard side in a span direction of the flap body and is inclined with respect to an aircraft axis direction, and a protruding portion that smoothly protrudes from a lower surface of the tip part on at least the outboard side. A rear end of the inclined portion is located closer to a side end edge of the tip part in the span direction of the flap body than a virtual line that passes through a front end of the inclined portion and is parallel to the aircraft axis direction.
    Type: Grant
    Filed: April 14, 2016
    Date of Patent: April 7, 2020
    Assignees: Mitsubishi Aircraft Corporation, Japan Aerospace Exploration Agency
    Inventors: Kensuke Hayashi, Mitsuhiro Murayama, Kazuomi Yamamoto
  • Patent number: 10604269
    Abstract: A structure for anti-adhesion of high-temperature air according to the present invention includes: a high-temperature air duct that is provided in an accessory of an aircraft and allows high-temperature air likely to be higher than a specified temperature to flow through the high-temperature air duct; an exhaust port that discharges a flow of the high-temperature air led through the high-temperature air duct, to an outside of the airframe; and a low-temperature air supplying part that supplies a flow of low-temperature air lower in temperature than the high-temperature air discharged to the outside of the airframe, to an airframe surface. The low-temperature air supplying part is configured to form an air layer made of a flow of low-temperature air between the high-temperature air that is bent toward the airframe surface in flight of the aircraft, and the an airframe surface.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: March 31, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Nobuhide Hara, Osamu Yamada
  • Patent number: 10591529
    Abstract: A wiring safety evaluation system that makes it possible to easily determine whether a plurality of electrical wires secured in redundancy belong to the same harness to evaluate wiring safety is provided. The wiring safety evaluation system according to the present invention includes a processing section that identifies, after an event ID is specified, whether a gate type of a parent ID corresponding to the event ID is an OR gate or an AND gate, and when the gate type is the OR gate, repeats a process procedure of identifying whether a gate type of a parent ID that is a parent in next generation of the parent ID is an OR gate or an AND gate to determine whether the specified event causes a top event.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: March 17, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Koji Toyama, Susumu Hirabayashi
  • Patent number: 10589866
    Abstract: An anti-icing system according to the present invention includes: a piccolo tube that includes a flow path through which heated gas flows in the 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 an engine serving as a supply source that supplies the heated gas toward the piccolo tube. The piccolo tube is decreased in an area of the flow path in a stepwise manner or in a continuous manner in the longitudinal direction, and has a continuous side surface provided with the ejection holes.
    Type: Grant
    Filed: December 27, 2016
    Date of Patent: March 17, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Masatoshi Morishita, Masanori Tsujita, Satoshi Watanabe, Yoichi Uefuji, Kazuhiro Kawai, Toshiyuki Ishida, Gento Ichikawa, Go Fujita
  • Patent number: 10583934
    Abstract: To provide a fuel pipe of an aircraft that makes it possible to maintain temperature of fuel in the fuel pipe at appropriate temperature while giving consideration to reliability that is constantly required for the aircraft. A fuel pipe provided in an airframe of the aircraft includes: an inner pipe defining a flow path through which fuel flows; and an outer pipe surrounding an outer periphery of the inner pipe. A gap is provided between the outer periphery of the inner pipe and an inner periphery of the outer pipe. The inner pipe is made of a rubber material, and the outer pipe is made of a metal material.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: March 10, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Nobuhide Hara, Ushio Komoda
  • Patent number: 10571025
    Abstract: A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft including a panel and a duct. The fire seal structure includes: a first member provided on the duct at a connection portion between the panel and the duct; and a second member that faces the first member around the opening and is provided on the panel. The panel defines the fire-prevention region. The duct communicates with an opening provided in the panel. The duct defines, together with the panel, the fire-prevention region. The first and the second members each contain refractory material, and the first and the second members form a labyrinth-shaped gap between the duct and the panel.
    Type: Grant
    Filed: December 5, 2017
    Date of Patent: February 25, 2020
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Akira Takeuchi
  • Patent number: 10532522
    Abstract: A method for molding a fiber-reinforced plastic member involves disposing a reinforced-fiber base material 2 inside a molding space S, which is created between a mold 1 and a bag film 6, and then depressurizing the inside of the molding space S and curing a resin composition R contained in the reinforced-fiber base material 2, wherein a flat pressure plate 5 made of spring steel is disposed between the reinforced-fiber base material 2 and the bag film 6. The pressure plate 5 elastically deforms along the shape of the reinforced-fiber base material 2 while the inside of the molding space S is being depressurized, and returns to its original flat shape when depressurization is stopped and the bag film 6 is removed after curing of the resin composition R.
    Type: Grant
    Filed: June 2, 2014
    Date of Patent: January 14, 2020
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Tomohiro Murai
  • Publication number: 20200002021
    Abstract: High-temperature gas exhausted to outside of an aircraft including exhaust air from an air conditioner is prevented from thermally influencing an airframe. An aircraft includes, in an airframe, an exhaust port configured to exhaust, to outside of the aircraft, high-temperature gas that flows through an exhaust duct provided in an air conditioner and has temperature higher than allowable temperature of GFRP used as a material of a fairing, and a partition as a turning reduction portion configured to reduce a turning component contained in flow of the high-temperature gas before the high-temperature gas is exhausted to the outside of the aircraft.
    Type: Application
    Filed: June 28, 2019
    Publication date: January 2, 2020
    Applicant: Mitsubishi Aircraft Corporation
    Inventor: Nobuhide Hara
  • Patent number: 10479516
    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).
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: November 19, 2019
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Tetsuya Oonishi, Masahiro Shimojo, Takanori Suzuki
  • Patent number: D870616
    Type: Grant
    Filed: April 26, 2017
    Date of Patent: December 24, 2019
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Hiroyasu Aruga