Patents by Inventor Jeffrey M. Roach

Jeffrey M. Roach 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: 20210276695
    Abstract: Control surface actuator assemblies, aircraft hydraulic systems including the same, and associated aircraft and methods. A control surface actuator assembly includes a flight control surface operatively coupled to a support structure, a torque-generating hydraulic actuator configured to apply a torque to pivot the flight control surface, and a variable horn radius (VHR) hydraulic actuator configured to vary an actuator moment arm length for pivoting the flight control surface. In some examples, an aircraft hydraulic system includes such control surface actuator assemblies, and an aircraft includes such aircraft hydraulic systems. In some examples, a method of operating one or more flight control surfaces of an aircraft includes controlling a selected flight control surface by adjusting, with a VHR hydraulic actuator, an actuator moment arm length corresponding to the selected flight control surface and pivoting, with a torque-generating hydraulic actuator, the selected flight control surface.
    Type: Application
    Filed: March 6, 2020
    Publication date: September 9, 2021
    Inventors: Michael Thomas Fox, Jeffrey M. Roach
  • Patent number: 11072418
    Abstract: A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: July 27, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10994857
    Abstract: Methods and apparatus to cool a vehicle heat source are disclosed herein. An example apparatus includes a first tank and a second tank. The first tank and the second tank are disposed on a vehicle. The second tank is in fluid communication with the first tank. An engine of the vehicle is to be supplied with fuel from at least one of the first tank or the second tank. The example apparatus also includes a cooling system disposed on the vehicle to cool the fuel flowing from the first tank to the second tank. The example apparatus further includes a heat exchanger operatively coupled to a heat source disposed on the vehicle. The fuel from the second tank is to flow to the first tank via the heat exchanger to cool the heat source.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: May 4, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Timothy Edward Bowman, William Webster Behrens, Thomas W. Omohundro, Jeffrey M. Roach
  • Patent number: 10947997
    Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include ports to receive and discharge hydraulic fluid. The dual spool valve may also include first and second valve sections that are selectively positionable to control the flow of hydraulic fluid into and out of the actuator. One position provides for hydraulic fluid to move through closure lines. Method of controlling the dual spool valve may provide for selectively positioning the valve sections to control the flow of hydraulic fluid, and to position the valve sections to move hydraulic fluid through a closure line during certain circumstances.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: March 16, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10851714
    Abstract: An accessory drive for an engine includes a power takeoff (PTO) configured to couple power from a rotating shaft of the engine and to convey the power through an opening in a housing of the engine. A gearbox is coupled to and configured to be driven by the PTO. The gearbox is disposed external to the housing and includes a planetary gear train. At least one engine accessory is coupled to and configured to be driven by the planetary gear train.
    Type: Grant
    Filed: April 29, 2019
    Date of Patent: December 1, 2020
    Assignee: The Boeing Company
    Inventors: Jeffrey M. Roach, Michael T. Fox, Howard Carter, III
  • Patent number: 10808789
    Abstract: There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft with a support structure. The translational inerter assembly includes a press fit element rotatably disposed within the flight control surface. The translational inerter assembly further includes an inertia element disposed in the press fit element. The translational inerter assembly further includes a torsion bar coupled to the inertia element and to the support structure of the aircraft, such that when the flight control surface rotates, the inertia element translates, and movement of the flight control surface is dampened.
    Type: Grant
    Filed: October 13, 2018
    Date of Patent: October 20, 2020
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Patent number: 10793261
    Abstract: An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: October 6, 2020
    Assignee: The Boeing Company
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10737764
    Abstract: Methods and devices for adjusting a position of a flight control member relative to a base of an aircraft. The devices and methods include a joint that movably connects the flight control surface to the base. An extension member is connected to the flight control surface and extends through the joint. Adjustable linear members of the base are connected to the extension member and configured to adjust the position of the extension member. This adjustment results in re-orienting the flight control member relative to the base to adjust the flight of the aircraft.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: August 11, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10723441
    Abstract: A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: July 28, 2020
    Assignee: The Boeing Company
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10711809
    Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include first and second manifolds that each includes a movable spool. Multiple ports are positioned in each of the manifolds. The movable spools are positionable within their respective manifolds to control the movement of the hydraulic fluid that is supplied to and removed from the hydraulic actuator.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: July 14, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10526071
    Abstract: The hydraulic system can include a control member that is operatively coupled to a member. The control member can include a hydraulic control member and an integrated inerter. Hydraulic fluid at variable pressures is moved through the hydraulic system by pumps. The hydraulic system can be configured for hydraulic fluid returning from the control member to the first pump to be delivered to the second pump prior to reaching the first pump. A dual-spool valve is positioned between the pumps and the control member to control the flow of the hydraulic fluid. The dual-spool valve is movable to move the hydraulic fluid at variable pressures into and out of first and second chambers of the control member. The dual spool valve can also be configured to operate the control member when a spool is not operational.
    Type: Grant
    Filed: April 13, 2018
    Date of Patent: January 7, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Patent number: 10526975
    Abstract: A power extraction system and method for a gas turbine engine of a vehicle are provided. The system has an HP spool tower shaft coupled between an HP spool of the gas turbine engine and an accessory gearbox assembly coupled to the gas turbine engine. The HP spool tower shaft extracts mechanical power from the HP spool. The system has an LP spool tower shaft coupled between an LP spool of the gas turbine engine and the accessory gearbox assembly. The LP spool tower shaft extracts mechanical power from the LP spool. The system further has the accessory gearbox assembly having an accessory drive combining the mechanical power from both the HP spool and LP spool, having a planetary gear train coupled to the accessory drive, and having one or more engine-driven accessories coupled to the planetary gear train and driven by a planetary gear train output to generate power.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: January 7, 2020
    Assignee: The Boeing Company
    Inventors: Eric A. Howell, Jeffrey M. Roach, Thomas W. Omohundro
  • Publication number: 20190315457
    Abstract: The hydraulic system can include a control member that is operatively coupled to a member. The control member can include a hydraulic control member and an integrated inerter. Hydraulic fluid at variable pressures is moved through the hydraulic system by pumps. The hydraulic system can be configured for hydraulic fluid returning from the control member to the first pump to be delivered to the second pump prior to reaching the first pump. A dual-spool valve is positioned between the pumps and the control member to control the flow of the hydraulic fluid. The dual-spool valve is movable to move the hydraulic fluid at variable pressures into and out of first and second chambers of the control member. The dual spool valve can also be configured to operate the control member when a spool is not operational.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190316607
    Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include ports to receive and discharge hydraulic fluid. The dual spool valve may also include first and second valve sections that are selectively positionable to control the flow of hydraulic fluid into and out of the actuator. One position provides for hydraulic fluid to move through closure lines. Method of controlling the dual spool valve may provide for selectively positioning the valve sections to control the flow of hydraulic fluid, and to position the valve sections to move hydraulic fluid through a closure line during certain circumstances.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190315456
    Abstract: A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190315455
    Abstract: An actuator assembly for an aircraft includes a support strut operatively coupled to a hinge axis of a flight control member of the aircraft, a hydraulic actuator operatively coupled to the flight control member via a pivot element, and an electro-mechanical actuator (EMA) having first and second opposing ends and a biasing member. The first end is operatively coupled to a support structure of the aircraft, and the second end is operatively coupled to both the support strut and the hydraulic actuator. The biasing member moves between a compressed state and an expanded state in response to a varying biasing load exerted on a surface of the flight control member, thereby reducing an amount of current needed to drive the EMA, as well as a number of high-pressure hydraulic cycles of the hydraulic actuator to control the flight control member.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190315454
    Abstract: A dual rack and pinion rotational inerter, configured to dampen the flutter of a flight control member of an aircraft, includes an inertial wheel and a brake member disposed on an inertial wheel. The brake member moves between a retracted position and a deployed position based on a rotational velocity of the inertial wheel. The brake member moves to the retracted position when the rotational velocity of the inertial wheel is slower than a predetermined threshold velocity to allow the rotation of the inertial wheel. When the rotational velocity of the inertial wheel is at least as fast as the predetermined threshold velocity, however, the brake member deploys to yieldingly resist the rotation of the inertial wheel. In either position, the inertial wheel causes the inerter to dampen the flutter.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190315450
    Abstract: Methods and devices for adjusting a position of a flight control member relative to a base of an aircraft. The devices and methods include a joint that movably connects the flight control surface to the base. An extension member is connected to the flight control surface and extends through the joint. Adjustable linear members of the base are connected to the extension member and configured to adjust the position of the extension member. This adjustment results in re-orienting the flight control member relative to the base to adjust the flight of the aircraft.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190316606
    Abstract: A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include first and second manifolds that each includes a movable spool. Multiple ports are positioned in each of the manifolds. The movable spools are positionable within their respective manifolds to control the movement of the hydraulic fluid that is supplied to and removed from the hydraulic actuator.
    Type: Application
    Filed: April 13, 2018
    Publication date: October 17, 2019
    Inventors: Michael Thomas Fox, Eric Anton Howell, Jeffrey M. Roach
  • Publication number: 20190257249
    Abstract: An accessory drive for an engine includes a power takeoff (PTO) configured to couple power from a rotating shaft of the engine and to convey the power through an opening in a housing of the engine. A gearbox is coupled to and configured to be driven by the PTO. The gearbox is disposed external to the housing and includes a planetary gear train. At least one engine accessory is coupled to and configured to be driven by the planetary gear train.
    Type: Application
    Filed: April 29, 2019
    Publication date: August 22, 2019
    Inventors: Jeffrey M. Roach, Michael T. Fox, Howard Carter, III