Patents Assigned to Mitsubishi Aircraft Corporation
  • Control system installed in aircraft, computer readable storage medium and aircraft
    Patent number: 9335763
    Abstract: To improve the reliability of a control in a control system for devices included in an aircraft, such as engines. An engine control system 10 for controlling engines 11 of an aircraft includes a FADEC 30 including a calculation processing unit 33 for performing control calculation, and a first memory 321 for storing abnormality detection information that indicates that the calculation processing unit 33 detects an abnormality occurred in a sensor 20 and an actuator 21 used for a control. The abnormality detection information is not erased but still stored in the first memory 321 since the first memory 321 is not cleared even if the engine 11 is stopped. As a result, referring to the abnormality detection information makes it possible to avoid using a device having a low reliability, in which an abnormality is detected, for the control.
    Type: Grant
    Filed: August 7, 2014
    Date of Patent: May 10, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Yoshihiro Nagashima
  • Wing panel and aircraft main wing
    Patent number: 9333550
    Abstract: There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member 20, a base part 21 is formed, and the neutral axis position N in the cross-sectional direction is located on the wing panel 11 side from the center position C in the height direction of a web part 22. When the peen forming method is carried out by projecting metal shots to a portion near a flange part 23 in the tip end portion of the stringer member 20, the tensile strain developing in the portion near a flange part 23 acts in a state in which the moment length around the neutral axis position N is kept long.
    Type: Grant
    Filed: January 22, 2014
    Date of Patent: May 10, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Hideto Motohashi, Yoshifumi Hosokawa, Toshinari Fujii
  • Anti-icing system and aircraft
    Patent number: 9334057
    Abstract: Provide is an anti-icing system that can cause anti-icing devices to properly operate even if a breakdown occurs in a switch after a pilot sets the switch. An anti-icing system of the present invention that controls operations of anti-icing devices provided in an aircraft includes: operation mode selecting means that selects an operation mode of the anti-icing devices; and control means that controls the operations of the anti-icing devices according to the operation mode selected by the operation mode selecting means. The operation mode includes at least a manual mode, an automatic mode, and a stop mode, and the control means controls the operations of the anti-icing devices in the automatic mode if detecting that a breakdown occurs in the operation mode selecting means when the manual mode or the stop mode is selected by the operation mode selecting means.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: May 10, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yoshihiro Nagashima, Noriyuki Enguchi, Shinichiro Asami
  • Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener
    Patent number: 9334065
    Abstract: There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A hole 32 is formed in a cap 30, and a screw groove 32a is formed in the hole 32. The configuration enables the cap 30 to be reliably and easily positioned and installed on a fastener member 24 and reliably prevents the cap 30 from coming off after the installation thereof. This improves the workability to reduce the production cost while assuring sufficient insulation properties and enables the cap 30 to be installed with stable quality irrespective of workers. Preferably, the cap 30 is made of a resin in view of mass producibility, weight reduction, and the like.
    Type: Grant
    Filed: July 11, 2013
    Date of Patent: May 10, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Masahiro Bessho, Wataru Nihimura, Naomoto Ishikawa, Yuichiro Kamino, Toshikatsu Nohara, Toru Hashigami, Tamaki Tsuzuki
  • Firewall, pylon of aircraft, and aircraft
    Patent number: 9334805
    Abstract: In order to provide a firewall that is capable of preventing flame passage through a through-hole without any sealant in a connecting part of a component in which a fastener through-hole is formed, a firewall 50 is provided which can prevent a flame from leaking out of the connecting part which connects a first member 51 to a second member 55, particularly through the fastener through-hole TH defined therein. In the firewall 50, the connecting part is a part of a fire-protection chamber 52. As sealing pieces 51d and 51e which also constitute a part of the fire-protection chamber 52 are in contact with each other, the flame is unable to enter into a closed space CA. Thus, the flame would not reach the connecting part, thereby preventing the flame from leaking out of the firewall 50 to the outside of a nacelle 23.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: May 10, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Akira Takeuchi
  • Lightning protection fastener and aircraft
    Patent number: 9290276
    Abstract: An aircraft of the present invention includes an outer panel 4 made of a fiber reinforced plastic material, a support member 5, and a lightning protection fastener 1. The fastener 1 includes a metal fastener body 2 having a shaft portion 10 and a head portion 20, and an insulating member 30 made of an insulating plastic material and mounted to the head portion 20. The portion 20 has a frustoconical-shaped fastener seat surface 211. The panel 4 includes a receiving surface 41 conforming to the fastener seat surface 211. The member 30 includes an insulating seat surface 321 retracted from a plane of the fastener seat surface 211 such that, when a portion 41A of the receiving surface 41 which is opposed to the fastener seat surface 211 is depressed, an insulating seat surface 321 comes into contact with the receiving surface 41.
    Type: Grant
    Filed: October 11, 2013
    Date of Patent: March 22, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yasunori Watanabe, Takamitsu Himeno, Hideo Yamakoshi
  • Nitrogen enriched air supply system and aircraft
    Patent number: 9272790
    Abstract: The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system produces NEA that is enriched with nitrogen upon supply of source gas during a flight through an ascent phase, a cruising phase, and a descent phase, and supplies the NEA to a fuel tank, the system including: an air separation module that separates oxygen and nitrogen in the source gas; and a temperature regulation mechanism that regulates a temperature of the source gas supplied to the air separation module. In at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism regulates the temperature of the source gas to below a temperature of the source gas in the descent phase.
    Type: Grant
    Filed: November 4, 2013
    Date of Patent: March 1, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Koki Fukuda
  • Aircraft fuel system and aircraft
    Patent number: 9254923
    Abstract: The present invention ensures explosion-proof performance without increasing the capacity for supplying nitrogen-enriched air in an aircraft fuel system having a ventilation function. An aircraft fuel system includes: fuel tanks; an NEA supply system; a left ventilation channel extending from a ventilation duct to a fuselage and leading into the tanks; and a right ventilation channel extending from a ventilation duct to the fuselage and leading into the tanks. The tank leading to the channel and the tank leading to the channel are separated by a central wall. The tanks communicate with each other through a fuel path, which allows, of fuel and gas, only the fuel to pass through, and float valves.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: February 9, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Junichiro Hashimoto, Ushio Komoda
  • Warning system for aircraft, and aircraft
    Patent number: 9254926
    Abstract: To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: February 9, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Naoto Maeda, Masaya Miyoshi
  • NITROGEN ENRICHED AIR SUPPLY SYSTEM AND AIRCRAFT
    Publication number: 20160009407
    Abstract: The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system produces NEA that is enriched with nitrogen upon supply of source gas during a flight through an ascent phase, a cruising phase, and a descent phase, and supplies the NEA to a fuel tank, the system including: an air separation module that separates oxygen and nitrogen in the source gas; and a temperature regulation mechanism that regulates a temperature of the source gas supplied to the air separation module. In at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism regulates the temperature of the source gas to below a temperature of the source gas in the descent phase.
    Type: Application
    Filed: November 4, 2013
    Publication date: January 14, 2016
    Applicant: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Koki FUKUDA
  • NITROGEN ENRICHED AIR SUPPLY SYSTEM AND AIRCRAFT
    Publication number: 20160009408
    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: Application
    Filed: November 4, 2013
    Publication date: January 14, 2016
    Applicant: Mitsubishi Aircraft Corporation
    Inventor: Koki FUKUDA
  • Inclination detection device for aircraft, and method for loading and unloading cargo using same
    Patent number: 9205930
    Abstract: An inclination detection device 11 for an aircraft includes a gravity sensor 13 that detects an inclination angle in a pitch direction at a parking time of a fuselage 1, an alarm device 16, and a control unit 17 that causes the device 16 to issue an alarm when the inclination angle detected by the sensor 13 approaches allowable limit inclination angles F4 and R4 in a forward inclination direction and a backward inclination direction of the fuselage 1. The control unit 17 has gravity center management information peculiar to the fuselage 1 inputted therein by a USB memory 20 or the like, and corrects a movable range in the forward and—backward inclination directions until the inclination angle reaches the angles F4 and R4 based on the gravity center management inclination information, before a loading and unloading operation of cargo into and from the fuselage 1.
    Type: Grant
    Filed: June 1, 2011
    Date of Patent: December 8, 2015
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Hiroki Yanagawa
  • Ceiling lighting apparatus of aircraft and aircraft
    Patent number: 9193300
    Abstract: To provide a ceiling lighting apparatus of an aircraft which can improve maintainability. The ceiling lighting apparatus includes: a ceiling panel 20 that is provided so as to be erected and laid with respect to a ceiling structure 14 that constitutes a ceiling structure of the aircraft with a hinge 15 as a rotation center; and a light 30 that is provided in the ceiling panel 20. A mechanic can perform maintenance of the light 30 in a comfortable posture with the ceiling panel 20 rotated to be suspended from a ceiling. Accordingly, the maintainability can be improved.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: November 24, 2015
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Hiroyasu Aruga, Takafumi Nakatani, Masashi Fujimoto, Zenji Hayakawa, Motohiko Kawaguchi, Toru Ando
  • Repair method and repair structure for honeycomb sandwich structural body
    Patent number: 9186756
    Abstract: A repair method includes the steps of: (A) forming a repair cavity 14 by removing a honeycomb core 11 including a damaged portion with a front-side skin 12; (B) inserting, into the repair cavity 14, a repair honeycomb core 21 whose end surface 30 on a side to which a repair patch 22 is bonded is subjected to flattening treatment; (C) disposing the repair patch on the flattened end surface 30 of the repair honeycomb core 21 via a film-like adhesive 24; and (D) bonding the repair honeycomb core 21 to an existing portion of the honeycomb sandwich structural body 10 and to the repair patch 22, and curing the repair patch 22 under a reduced-pressure atmosphere associated with heating.
    Type: Grant
    Filed: November 22, 2012
    Date of Patent: November 17, 2015
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Toshikazu Shigetomi
  • JIG FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, METHOD FOR FORMING SEALANT LAYER FOR LIGHTNING PROTECTION FASTENER, LIGHTNING PROTECTION FASTENER, AND WING OF AIRCRAFT
    Publication number: 20150298819
    Abstract: To provide a jig for forming a sealant layer for a lightning protection fastener which enables to quickly and accurately obtain a sealant layer having a required thickness. A guide jig 30 is used to form a sealant layer 29 around a fastener member 24 that passes through and fastens a plurality of members constituting an airframe of an aircraft, the jig including: a cup 31 including a cavity 33 to be filled with an uncured sealant 28; and a guide that is provided within the cavity 33 and engaged with the fastener member 24 so as to match a center axis of the cavity 33 with a center axis of the fastener member 24.
    Type: Application
    Filed: January 28, 2014
    Publication date: October 22, 2015
    Applicant: Mitsubishi Aircraft Corporation
    Inventors: Hideo Yamakoshi, Yuji Asahara, Wataru Nishimura, Takeyasu Tarumi, Noritomo Takata, Jun Kawaguchi, Hiroshi Rikukawa, Tomonori Okumura, Kengo Nomiya
  • Lightning protection fastener and cap for lightning protection fastener
    Patent number: 9163656
    Abstract: To provide a lightning protection fastener or the like, that can reliably seal an arc between the cap and a member such as a wing panel. An end part 30A of a cap 30 on an opening side, the end part 30 A facing a member 22 (or member 21), includes a plane 30d orthogonal to an axis line of the cap 30A and a tapered face 30c formed on an outer circumferential side of the plane 30d. A sealant 34 that spills out of the cap 30A upon mounting the cap 30A is present between the tapered face 30c and a surface 22f of the member 22 (sealant 34S).
    Type: Grant
    Filed: November 1, 2012
    Date of Patent: October 20, 2015
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yuji Asahara, Hideo Yamakoshi, Atsuhiro Iyomasa, Takeyasu Tarumi, Wataru Nishimura, Yasunori Watanabe, Toru Hashigami, Hiroshi Rikukawa, Hideo Imamura, Naoki Taniguchi
  • Warning system of aircraft and aircraft
    Patent number: 9120582
    Abstract: A warning system 10 that warns of saturation of the control capability for the moving surface such as an elevator 4 and a rudder 8 of an aircraft has a determination section 31 that determines whether or not the control capability for the moving surface is saturated, and a display 50 that issues a warning when the determination section 31 determines that the control capability for the moving surface is saturated. The determination section 31 determines that the control capability for the elevator 4 is saturated, when a control target position of the elevator 4 by, for example, a control stick (column) is larger than a first reference position indicating an operation limit of the elevator 4, and a present position of the column is smaller than a second reference position indicating an operation limit of the column.
    Type: Grant
    Filed: February 21, 2014
    Date of Patent: September 1, 2015
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Masaya Miyoshi
  • WARNING SYSTEM OF AIRCRAFT AND AIRCRAFT
    Publication number: 20150175273
    Abstract: A warning system 10 that warns of saturation of the control capability for the moving surface such as an elevator 4 and a rudder 8 of an aircraft has a determination section 31 that determines whether or not the control capability for the moving surface is saturated, and a display 50 that issues a warning when the determination section 31 determines that the control capability for the moving surface is saturated. The determination section 31 determines that the control capability for the elevator 4 is saturated, when a control target position of the elevator 4 by, for example, a control stick (column) is larger than a first reference position indicating an operation limit of the elevator 4, and a present position of the column is smaller than a second reference position indicating an operation limit of the column.
    Type: Application
    Filed: February 21, 2014
    Publication date: June 25, 2015
    Applicant: Mitsubishi Aircraft Corporation
    Inventor: Masaya MIYOSHI
  • Outlet of air conditioning for aircraft
    Patent number: D746972
    Type: Grant
    Filed: June 18, 2013
    Date of Patent: January 5, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Hiroyasu Aruga
  • Outlet of air conditioning for aircraft
    Patent number: D754839
    Type: Grant
    Filed: July 31, 2015
    Date of Patent: April 26, 2016
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Hiroyasu Aruga