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: 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
  • Patent number: 10352389
    Abstract: There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft having a support structure. The system has a flexible holding structure disposed between the flight control surface and the support structure. The system has a dual rack and pinion assembly held by the flexible holding structure. The system has a first terminal and a second terminal, coupled to the dual rack and pinion assembly. The first terminal is coupled to the flight control surface. The system has a pair of inertia wheels coupled to the flexible holding structure. The system has an axle element inserted through the inertia wheels, the flexible holding structure, and the dual rack and pinion assembly, such that when the flight control surface rotates, the dual rack and pinion rotational inerter system translates and rotates, and movement of the flight control surface is dampened.
    Type: Grant
    Filed: October 13, 2018
    Date of Patent: July 16, 2019
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Patent number: 10337581
    Abstract: An apparatus for damping an actuator includes an inerter. The inerter includes a first terminal and a second terminal movable relative to one another and configured to be mutually exclusively coupled to a support structure and a movable device actuated by an actuator. The inerter further includes a threaded shaft coupled to and movable along the inerter axis with one of the first terminal and the second terminal. The inerter additionally includes a flywheel rotatable in proportion to movement of the threaded shaft in response to axial acceleration of the first terminal relative to the second terminal during actuation of the movable device by the actuator. The inerter reduces actuator-load-oscillatory amplitude at resonance of the actuator and movable device relative to the actuator-load-oscillatory amplitude that would otherwise occur using the same actuator without an inerter.
    Type: Grant
    Filed: August 25, 2018
    Date of Patent: July 2, 2019
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach
  • Patent number: 10273883
    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: February 26, 2016
    Date of Patent: April 30, 2019
    Assignee: The Boeing Company
    Inventors: Jeffrey M. Roach, Michael T. Fox, Howard Carter, III
  • Publication number: 20190048959
    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: Application
    Filed: October 13, 2018
    Publication date: February 14, 2019
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Publication number: 20190048961
    Abstract: There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft having a support structure. The system has a flexible holding structure disposed between the flight control surface and the support structure. The system has a dual rack and pinion assembly held by the flexible holding structure. The system has a first terminal and a second terminal, coupled to the dual rack and pinion assembly. The first terminal is coupled to the flight control surface. The system has a pair of inertia wheels coupled to the flexible holding structure. The system has an axle element inserted through the inertia wheels, the flexible holding structure, and the dual rack and pinion assembly, such that when the flight control surface rotates, the dual rack and pinion rotational inerter system translates and rotates, and movement of the flight control surface is dampened.
    Type: Application
    Filed: October 13, 2018
    Publication date: February 14, 2019
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Publication number: 20190003548
    Abstract: An apparatus for damping an actuator includes an inerter. The inerter includes a first terminal and a second terminal movable relative to one another and configured to be mutually exclusively coupled to a support structure and a movable device actuated by an actuator. The inerter further includes a threaded shaft coupled to and movable along the inerter axis with one of the first terminal and the second terminal. The inerter additionally includes a flywheel rotatable in proportion to movement of the threaded shaft in response to axial acceleration of the first terminal relative to the second terminal during actuation of the movable device by the actuator. The inerter reduces actuator-load-oscillatory amplitude at resonance of the actuator and movable device relative to the actuator-load-oscillatory amplitude that would otherwise occur using the same actuator without an inerter.
    Type: Application
    Filed: August 25, 2018
    Publication date: January 3, 2019
    Inventors: Michael T. Fox, Jeffrey M. Roach
  • Patent number: 10145434
    Abstract: There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.
    Type: Grant
    Filed: January 11, 2018
    Date of Patent: December 4, 2018
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Patent number: 10107347
    Abstract: There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft. The system has a flexible holding structure disposed between the flight control surface and a support structure of the aircraft. The system has a dual rack and pinion assembly held by and between the flexible holding structure. The dual rack and pinion assembly has a first rack, a second rack, and a pinion engaged to and between the racks. The system has a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure. The system has a pair of inertia wheels adjacent the flexible holding structure. The system has an axle element inserted through the inertial wheels, the flexible holding structure, and the pinion.
    Type: Grant
    Filed: January 11, 2018
    Date of Patent: October 23, 2018
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Patent number: 10088006
    Abstract: An apparatus for damping an actuator includes an inerter. The inerter includes a first terminal and a second terminal movable relative to one another along an inerter axis and configured to be mutually exclusively coupled to a support structure and a movable device actuated by an actuator. The inerter further includes a rod coupled to and movable with the first terminal and a threaded shaft coupled to and movable with the second terminal. The inerter further includes a flywheel having a flywheel annulus coupled to one of the rod and the threaded shaft. The flywheel is configured to rotate in proportion to axial acceleration of the rod relative to the threaded shaft in correspondence with actuation of the movable device by the actuator.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: October 2, 2018
    Assignee: The Boeing Company
    Inventors: Michael T. Fox, Jeffrey M. Roach
  • Patent number: 10081439
    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: June 20, 2013
    Date of Patent: September 25, 2018
    Assignee: The Boeing Company
    Inventors: Timothy Edward Bowman, William Webster Behrens, Thomas W. Omohundro, Jeffrey M. Roach
  • Publication number: 20180155046
    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: Application
    Filed: January 19, 2018
    Publication date: June 7, 2018
    Inventors: Timothy Edward Bowman, William Webster Behrens, Thomas W. Omohundro, Jeffrey M. Roach
  • Publication number: 20180156293
    Abstract: There is provided a dual rack and pinion rotational inerter system for damping movement of a flight control surface of an aircraft. The system has a flexible holding structure disposed between the flight control surface and a support structure of the aircraft. The system has a dual rack and pinion assembly held by and between the flexible holding structure. The dual rack and pinion assembly has a first rack, a second rack, and a pinion engaged to and between the racks. The system has a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure. The system has a pair of inertia wheels adjacent the flexible holding structure. The system has an axle element inserted through the inertial wheels, the flexible holding structure, and the pinion.
    Type: Application
    Filed: January 11, 2018
    Publication date: June 7, 2018
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Publication number: 20180149091
    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: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Inventors: Eric A. Howell, Jeffrey M. Roach, Thomas W. Omohundro
  • Publication number: 20180135717
    Abstract: There is provided a translational inerter assembly for damping movement of a flight control surface of an aircraft. The assembly has a press fit element fixedly disposed within a first end of the flight control surface and rotatably movable with the flight control surface. The assembly further has an inertia element coupled to and installed in the press fit element. The assembly further has a torsion bar having a torsion bar first end coupled to and installed in the inertia element, and having a torsion bar second end fixedly attached to a support structure of the aircraft. Rotation of the flight control surface causes translational movement of the inertia element, via the press fit element, along a hinge axis of the flight control surface and along the torsion bar, resulting in the translational inerter assembly damping movement of the flight control surface.
    Type: Application
    Filed: January 11, 2018
    Publication date: May 17, 2018
    Inventors: Michael T. Fox, Jeffrey M. Roach, Eric A. Howell
  • Publication number: 20170335916
    Abstract: An apparatus for damping an actuator includes an inerter. The inerter includes a first terminal and a second terminal movable relative to one another along an inerter axis and configured to be mutually exclusively coupled to a support structure and a movable device actuated by an actuator. The inerter further includes a rod coupled to and movable with the first terminal and a threaded shaft coupled to and movable with the second terminal. The inerter further includes a flywheel having a flywheel annulus coupled to one of the rod and the threaded shaft. The flywheel is configured to rotate in proportion to axial acceleration of the rod relative to the threaded shaft in correspondence with actuation of the movable device by the actuator.
    Type: Application
    Filed: May 19, 2016
    Publication date: November 23, 2017
    Inventors: Michael T. Fox, Jeffrey M. Roach
  • Publication number: 20170248081
    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: February 26, 2016
    Publication date: August 31, 2017
    Inventors: Jeffrey M. Roach, Michael T. Fox, Howard Carter, III
  • Patent number: 8876063
    Abstract: A flight control system for an aircraft directs a primary surface that is pivotable with respect to the aircraft with a moveable tab located at the end of the primary surface. A primary surface actuator maintains a position of the primary surface. A tab actuator moves the tab with respect to the primary flight control surface. A controller configured to coordinate the movement of the primary flight control surface with the movement of the tab by deflecting the tab with respect to the primary flight control surface, thereby allowing aerodynamic forces acting upon the deflected tab to position the primary flight control surface at a desired position. The primary flight control surface can then be maintained at the desired position by the primary surface actuator.
    Type: Grant
    Filed: December 10, 2007
    Date of Patent: November 4, 2014
    Assignee: The Boeing Company
    Inventors: James J. Sheahan, Jr., Charles E. Morris, Jeffrey M. Roach
  • Patent number: 8710786
    Abstract: An actuator motor described herein has fast dynamic response capability, high torque density, high efficiency, and improved thermal and mechanical stability at high speed while minimizing weight. According to one aspect of the disclosure provided herein, an actuator motor has a rotor shaft with an array of permanent magnets attached according to a Halbach array configuration. A stator includes windings that induce a torque on the rotor shaft when rotating magnetic fields interact with the optimized magnetic flux distributions of the magnets of the Halbach array. According to various embodiments, the rotor shaft is hollow, reducing weight and rotational inertia, while improving ambient cooling characteristics of the motor.
    Type: Grant
    Filed: May 20, 2013
    Date of Patent: April 29, 2014
    Assignee: The Boeing Company
    Inventors: Leila Parsa, Jeffrey M. Roach, Kamiar J. Karimi, Shengyi Liu, Suman Dwari
  • Patent number: 8567714
    Abstract: Systems and techniques are described for actuating a control surface about a pivot point using variable moments. A bracket having a moment arm is coupled to the pivot point such that the bracket is rotatable about the pivot point to actuate the surface. A power actuator has a shaft coupled to the bracket at a coupling point on the moment arm such that actuation force applied to the shaft results in a moment produced about the pivot point. A linear actuator is configured to adjust the location of the coupling point with respect to the pivot point to thereby changing the moment arm and the moment produced about the pivot point as the bracket rotates. By adjusting the distance between the pivot point and the coupling point, the moments produced about the pivot point can be increased while conserving actuator power.
    Type: Grant
    Filed: December 7, 2007
    Date of Patent: October 29, 2013
    Assignee: The Boeing Company
    Inventors: James J. Sheahan, Jr., Charles E. Morris, Jeffrey M. Roach, Howard Carter