Patents Assigned to Mitsubishi Aircraft Corporation
  • FLAP AND AIRCRAFT
    Publication number: 20180155007
    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: Application
    Filed: April 14, 2016
    Publication date: June 7, 2018
    Applicants: MITSUBISHI AIRCRAFT CORPORATION, Japan Aerospace Exploration Agency
    Inventors: Kensuke Hayashi, Mitsuhiro Murayama, Kazuomi Yamamoto
  • AIRCRAFT FIRE SEAL STRUCTURE AND AIRCRAFT
    Publication number: 20180156334
    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: Application
    Filed: December 5, 2017
    Publication date: June 7, 2018
    Applicant: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Akira Takeuchi
  • AIRCRAFT FIRE SEAL STRUCTURE AND AIRCRAFT
    Publication number: 20180156129
    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: Application
    Filed: December 5, 2017
    Publication date: June 7, 2018
    Applicant: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Akira Takeuchi
  • Water-inflow prevention device of aircraft, air pressure regulating valve for aircraft, and aircraft
    Patent number: 9969498
    Abstract: A water-inflow prevention device is provided by installing a closing lid 6 for blocking a duct 2 of an air pressure regulating valve 1, which regulates air pressure inside a cabin 101. A buoyant body 9 is attached to the disc-shaped closing lid 6 installed to the duct 2 so as to be rotatable around a rotation shaft 7. The buoyant body 9 receives a buoyant force from water when immersed in the water. Since the side of the closing lid 6 in which the buoyant body 9 is attached is thereby floated in the water, the closing lid 6 automatically rotates around the rotation shaft 7 so as to close a ventilation port 2a.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: May 15, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Shingo Kawano, Tomoka Mashio, Akitaka Urano, Shuichi Hagino
  • Flap deploying device and aircraft
    Patent number: 9963220
    Abstract: The flap deploying device for a flap disposed at a leading edge or a trailing edge of a main wing of the aircraft, the deploying device including: a drive source; a moving mechanism with a moving body advancing and retracting by power of the drive source; a carriage mechanism that carries advancing and retracting motion of the moving body to the flap so as to deploy the flap between a retracted position and a deployed position; and a rail that guides the carriage mechanism. Since the moving mechanism is arranged lateral to the rail in the wingspan direction of the main wing, the dimension of the wing in a thickness direction can be reduced at least by a dimension corresponding to the moving mechanism. Therefore, the wing can be made thinner, or the projecting height of a flap track fairing can be reduced.
    Type: Grant
    Filed: December 13, 2013
    Date of Patent: May 8, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Kenya Ishihara, Zenta Sugawara
  • Nitrogen enriched air supply system and aircraft
    Patent number: 9963239
    Abstract: To provide a system which supplies nitrogen enriched air (NEA) produced by using bleed air as a supply source of the NEA to a fuel tank, and which can further improve the fuel consumption. The present invention employs an NEA supply system 10 that controls a supply in a flow control valve (FCV) 11 so as to obtain a supply flow rate Fs as a value obtained by adding a small margin flow rate Fm to a required amount Fn of nitrogen enriched air required to be supplied to a first fuel tank 15, in at least a part of a descent phase of an aircraft 100. Accordingly, explosion of the first fuel tank 15 can be prevented, and the fuel consumption of an engine 1 can be improved in the descent phase.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: May 8, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Koki Fukuda
  • Aircraft floor panel with ball transfer unit
    Patent number: 9963232
    Abstract: A floor panel apparatus comprises: beams arranged inside an aircraft main body; floor panels arranged on the beams; and ball transfer unit bolts each including a ball transfer unit in which a rotatable ball is disposed and a bolt portion which is integral with the ball transfer unit, the ball transfer unit bolts configured such that the floor panels and the beams are detachably fastened together by the bolt portions with the balls protruding on the floor panel side.
    Type: Grant
    Filed: January 25, 2016
    Date of Patent: May 8, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Bachhao Rajeev
  • Fuel tank, fuel pipe, and aircraft
    Patent number: 9957059
    Abstract: A fuel tank that stores fuel to be fed to a fuel supply destination through a pipe, wherein a whole or a portion of a storage fuel contact portion in contact with the fuel within the fuel tank is subjected to surface finishing for imparting hydrophilicity.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: May 1, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Shingo Kawano, Atsushi Fujii, Yuichi Kanemaki, Ushio Komoda, Toshiyuki Umemoto
  • Windshield of aircraft
    Patent number: 9957034
    Abstract: The present invention provides a windshield of an aircraft, including a plurality of conductive members that are disposed along an in-plane direction of the windshield, and are wire-connected together, wherein the plurality of conductive members are heaters that generate heat when supplied with an alternating current, and the conductive members are wire-connected such that induced currents induced in the respective conductive members by a magnetic field in association with a lightning current are circulated between the conductive members.
    Type: Grant
    Filed: December 22, 2015
    Date of Patent: May 1, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Taketoshi Yamaura, Katsuya Kitazume, Masaki Hashimoto
  • Door of aircraft and aircraft having the same
    Patent number: 9957033
    Abstract: A fence 30A is installed on an inner surface 21a of a door 20A on the side which faces a landing gear bay 15, the fence 30A rising inwardly of the airframe from the inner surface 21a. When the door 20A opens outwardly of an airframe due to a pressure difference between the side of an outer surface 21c of the door 20A and the side of an inner surface 21a facing inner part of the landing gear bay 15 during a flight of an aircraft 10, the fence 30A closes a gap between the door 20A and an opening 15a of the landing gear bay 15, and thereby prevents air from flowing into the landing gear bay 15 through the gap.
    Type: Grant
    Filed: January 14, 2013
    Date of Patent: May 1, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Ichiro Maeda, Hirofumi Maeda
  • Electric wire protecting device
    Patent number: 9953748
    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.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: April 24, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Syusaku Yamamoto, Ko Yatabe
  • Aircraft
    Patent number: 9933073
    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.
    Type: Grant
    Filed: March 4, 2015
    Date of Patent: April 3, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Shingo Goto, Toshiaki Sugimura
  • Vent member, wing panel, and main wing for aircraft
    Patent number: 9926082
    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.
    Type: Grant
    Filed: November 27, 2012
    Date of Patent: March 27, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Ushio Komoda, Hideto Motohashi
  • Aircraft antenna cover, aircraft member cover, aircraft, and rain erosion boot for aircraft
    Patent number: 9896220
    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.
    Type: Grant
    Filed: March 27, 2015
    Date of Patent: February 20, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Takashi Yokoi
  • Aircraft including support for a fairing
    Patent number: 9889921
    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.
    Type: Grant
    Filed: August 18, 2015
    Date of Patent: February 13, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Keiji Nakashima
  • Electric wire structure and method for electromagnetic shielding of electric wire
    Patent number: 9892826
    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.
    Type: Grant
    Filed: February 4, 2015
    Date of Patent: February 13, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Kazunori Teshima, Katsuya Kitazume
  • Heat removal structure of aircraft main landing gear bay
    Patent number: 9868534
    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.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: January 16, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Nobuhide Hara, Tadahiko Suzuta
  • Water inflow prevention device for aircraft working when landing in water, pressure adjusting valve, and aircraft
    Patent number: 9868538
    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.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: January 16, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Shimpei Todaka, Shingo Kawano, Takashi Uchino, Kiyonori Kushioka, Tsutomu Kawamizu, Atsushi Fujii, Yuta Takahashi, Shuichi Hagino, Akitaka Urano
  • Mandrel
    Patent number: 9862016
    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.
    Type: Grant
    Filed: March 3, 2016
    Date of Patent: January 9, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Hiroshi Kawamoto, Toyoaki Yasui, Kunihiro Kuroi, Tomone Kishida
  • Aircraft including turbofan engine and igniter cable
    Patent number: 9856031
    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.
    Type: Grant
    Filed: February 5, 2015
    Date of Patent: January 2, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Jingo Tateiwa