Patents by Inventor Gen Matsui

Gen Matsui has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Publication number: 20200012298
    Abstract: A system and method of controlling a position of a structure. A position command indicating a desired position for the structure and a position feedback signal indicating the position of the structure are received. A position control signal is generated based on a difference between the desired position and the position indicated by the position feedback signal. A stop feedback signal relative to the position of the structure is received. A stop control signal is generated based on the stop feedback signal and a stop condition for the structure. One of the position control signal and the stop control signal is selected. The selected one of the position control signal and the stop control signal is provided to an actuator for controlling the position of the structure.
    Type: Application
    Filed: August 30, 2019
    Publication date: January 9, 2020
    Inventor: Gen Matsui
  • Publication number: 20190363153
    Abstract: A display device includes a TFT layer provided in a display area, a bending section and a terminal in a non-active area, and a terminal wiring line that connects to the terminal through the bending section, and the terminal wiring line includes a first wiring line and a second wiring line each positioned on both sides of the bending section and a third wiring line that passes through the bending section and is electrically connected with each of the first wiring line and the second wiring line and curved so as to have recesses and protrusions.
    Type: Application
    Filed: September 22, 2017
    Publication date: November 28, 2019
    Inventors: Takashi MATSUI, Yukio SHIMIZU, Gen NAGAOKA, Motoji SHIOTA
  • Patent number: 10401875
    Abstract: A system and method of controlling a position of a structure. A position command indicating a desired position for the structure and a position feedback signal indicating the position of the structure are received. A position control signal is generated based on a difference between the desired position and the position indicated by the position feedback signal. A stop feedback signal relative to the position of the structure is received. A stop control signal is generated based on the stop feedback signal and a stop condition for the structure. One of the position control signal and the stop control signal is selected. The selected one of the position control signal and the stop control signal is provided to an actuator for controlling the position of the structure.
    Type: Grant
    Filed: July 31, 2014
    Date of Patent: September 3, 2019
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Publication number: 20190004515
    Abstract: A method and system for managing a control system having triple redundancy for an aircraft. The method comprises receiving a group of messages from a transmitting lane in a controller including three lanes in which a first lane failure has previously occurred. The method identifies an activity indicator, a status generated by each lane in a group of lanes, and a cyclic redundancy check value generated by each lane in the group of lanes in the group of messages. The cyclic redundancy check value generated by a lane in the group of lanes is generated using a key assigned to the lane. The method disables the controller when at least one of an anomaly is indicated in the status, an activity indicator mismatch is present, or a cyclic redundancy check value mismatch is present in the group of messages that indicates a second lane failure has occurred.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 3, 2019
    Inventor: Gen Matsui
  • Publication number: 20180143655
    Abstract: The electronic device includes a temperature sensor and a controller. The controller acquires temperature detected by the temperature sensor when transitioning to the predetermined mode. When the temperature is equal to or higher than a temperature judgment value, the controller performs a plurality of functions corresponding to the predetermined mode. When the temperature is lower than the temperature judgment value, the controller performs a subset of the plurality of functions.
    Type: Application
    Filed: November 20, 2017
    Publication date: May 24, 2018
    Inventor: Gen MATSUI
  • Patent number: 9548152
    Abstract: A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current.
    Type: Grant
    Filed: July 20, 2015
    Date of Patent: January 17, 2017
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Patent number: 9493231
    Abstract: An apparatus and method for controlling an actuator. A plurality of commands for the actuator are received from a number of primary controllers by a command lane and a monitor lane. The command lane selects a first selected number of commands from the plurality of commands using a selection rule. The monitor lane selects a second selected number of commands from the plurality of commands using the selection rule and generates a check value for the second selected number of commands. The first selected number of commands from the command lane and the check value from the monitor lane are combined to form an actuator control command message comprising the first selected number of commands and the check value. The actuator control command message is sent to an actuator controller for controlling the actuator.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: November 15, 2016
    Assignee: THE BOEING COMPANY
    Inventor: Gen Matsui
  • Publication number: 20160272300
    Abstract: An apparatus and method for controlling an actuator. A plurality of commands for the actuator are received from a number of primary controllers by a command lane and a monitor lane. The command lane selects a first selected number of commands from the plurality of commands using a selection rule. The monitor lane selects a second selected number of commands from the plurality of commands using the selection rule and generates a check value for the second selected number of commands. The first selected number of commands from the command lane and the check value from the monitor lane are combined to form an actuator control command message comprising the first selected number of commands and the check value. The actuator control command message is sent to an actuator controller for controlling the actuator.
    Type: Application
    Filed: March 20, 2015
    Publication date: September 22, 2016
    Inventor: Gen Matsui
  • Publication number: 20160031547
    Abstract: A system and method of controlling a position of a structure. A position command indicating a desired position for the structure and a position feedback signal indicating the position of the structure are received. A position control signal is generated based on a difference between the desired position and the position indicated by the position feedback signal. A stop feedback signal relative to the position of the structure is received. A stop control signal is generated based on the stop feedback signal and a stop condition for the structure. One of the position control signal and the stop control signal is selected. The selected one of the position control signal and the stop control signal is provided to an actuator for controlling the position of the structure.
    Type: Application
    Filed: July 31, 2014
    Publication date: February 4, 2016
    Inventor: Gen Matsui
  • Publication number: 20150325353
    Abstract: A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current.
    Type: Application
    Filed: July 20, 2015
    Publication date: November 12, 2015
    Inventor: Gen Matsui
  • Patent number: 9117579
    Abstract: A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current.
    Type: Grant
    Filed: July 16, 2013
    Date of Patent: August 25, 2015
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Publication number: 20150021441
    Abstract: A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current.
    Type: Application
    Filed: July 16, 2013
    Publication date: January 22, 2015
    Inventor: Gen Matsui
  • Patent number: 8855943
    Abstract: A system and methods for actuator fatigue monitoring is disclosed. At least two measured actuator forces are received from at least two actuators respectively, and a hybrid force is calculated. The hybrid force is calculated based on a force fight of the at least two actuators calculated based on the at least two measured actuator forces, and a monitored actuator force among the at least two measured actuator forces. An air load of the at least two actuators is estimated based on the at least two measured actuator forces, and a fatigue anomaly is determined based on the hybrid force and the air load.
    Type: Grant
    Filed: October 31, 2011
    Date of Patent: October 7, 2014
    Assignee: The Boeing Company
    Inventors: Gen Matsui, Douglas B. Kirkland
  • Patent number: 8683860
    Abstract: A system and methods for non-optimal actuator detection are disclosed. A fluid valve controlling a fluid flow to a first actuator is activated, and the fluid valve is controlled to move the first actuator from an initial position to a first position and back to the initial position during a test interval. A measured valve position of the fluid valve is measured during the test interval, and a measured valve travel is calculated based on the measured valve position at an end of the test interval. A health status of the first actuator is determined based on the measured valve travel and an expected valve travel.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: April 1, 2014
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Patent number: 8644767
    Abstract: A system and methods for wraparound signal monitoring are presented. An initial signal is transmitted through a signal path to provide a transmitted signal, and the transmitted signal is transmitted through an inverse signal path to provide an inverse signal. The inverse signal path comprises an inverse of the signal path. The transmitted signal is filtered to provide a filtered signal, and the filtered signal is transmitted through the inverse signal path to provide an inverse filtered signal. The inverse signal, the inverse filtered signal, and the initial signal are compared to provide a signal status.
    Type: Grant
    Filed: April 5, 2012
    Date of Patent: February 4, 2014
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Patent number: 8620522
    Abstract: Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft.
    Type: Grant
    Filed: May 25, 2011
    Date of Patent: December 31, 2013
    Assignee: The Boeing Company
    Inventor: Gen Matsui
  • Publication number: 20130104991
    Abstract: A system and methods for non-optimal actuator detection are disclosed. A fluid valve controlling a fluid flow to a first actuator is activated, and the fluid valve is controlled to move the first actuator from an initial position to a first position and back to the initial position during a test interval. A measured valve position of the fluid valve is measured during the test interval, and a measured valve travel is calculated based on the measured valve position at an end of the test interval. A health status of the first actuator is determined based on the measured valve travel and an expected valve travel.
    Type: Application
    Filed: October 28, 2011
    Publication date: May 2, 2013
    Inventor: Gen Matsui
  • Publication number: 20120303210
    Abstract: Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft.
    Type: Application
    Filed: May 25, 2011
    Publication date: November 29, 2012
    Inventor: Gen Matsui
  • Publication number: 20110290938
    Abstract: Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control means for producing a control signal in accordance with the instruction signal; and switching means for selectively switching one of the primary control means and the secondary control means to the other, and in which the secondary control means is less in the number of functions than the primary control means, and each of components constituting the secondary control means is easier in fault verification than a component constituting the primary control means the most difficult in fault verification among all of components constituting the primary control means.
    Type: Application
    Filed: April 6, 2010
    Publication date: December 1, 2011
    Applicants: Nabtesco Aerospace, Inc., Nabtesco Corporation
    Inventors: Gen Matsui, Teruaki Tanaka, Tsuyoshi Yamamoto
  • Patent number: 7870726
    Abstract: A backup system is provided that has a local electric motor and pump for some or all of hydraulic actuators. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.
    Type: Grant
    Filed: July 14, 2009
    Date of Patent: January 18, 2011
    Assignee: Nabtesco Corporation
    Inventor: Gen Matsui