Patents by Inventor Michael A. Barker

Michael A. Barker 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).

  • Patent number: 9429105
    Abstract: A rocket vehicle includes a controller that integrates operation of a variable-vector main thruster and attitude control thrusters. When the main thruster is firing and roll is commanded, the controller can provide roll moment by firing only a single attitude control thruster, while changing the thrust vector of the main thruster to offset any pitch/yaw moments induced by the firing of the single attitude control thruster. The single attitude control thruster may be a thruster on the leeward side of the rocket vehicle. Since there is a lower wall pressure on the leeward side of the rocket vehicle, the thruster efficiency is improved by accomplishing roll by use of a single thruster (which may be one of a pair of thrusters used to achieve roll in one direction). A significant reduction in fuel use may be accomplished.
    Type: Grant
    Filed: June 7, 2013
    Date of Patent: August 30, 2016
    Assignee: Raytheon Company
    Inventors: Michael A Barker, Dean W Smith, Edward J Marquart, Joseph R Corrado
  • Patent number: 9377279
    Abstract: A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.
    Type: Grant
    Filed: April 22, 2014
    Date of Patent: June 28, 2016
    Assignee: Raytheon Company
    Inventors: Andrew B. Facciano, William G. Graves, Michael A. Barker, Michael S. Alkema, Jeffrey S. Larson
  • Publication number: 20150300780
    Abstract: A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.
    Type: Application
    Filed: April 22, 2014
    Publication date: October 22, 2015
    Applicant: Raytheon Company
    Inventors: Andrew B. Facciano, William G. Graves, Michael A. Barker, Michael S. Alkema, Jeffrey S. Larson
  • Publication number: 20140360157
    Abstract: A rocket vehicle includes a controller that integrates operation of a variable-vector main thruster and attitude control thrusters. When the main thruster is firing and roll is commanded, the controller can provide roll moment by firing only a single attitude control thruster, while changing the thrust vector of the main thruster to offset any pitch/yaw moments induced by the firing of the single attitude control thruster. The single attitude control thruster may be a thruster on the leeward side of the rocket vehicle. Since there is a lower wall pressure on the leeward side of the rocket vehicle, the thruster efficiency is improved by accomplishing roll by use of a single thruster (which may be one of a pair of thrusters used to achieve roll in one direction). A significant reduction in fuel use may be accomplished.
    Type: Application
    Filed: June 7, 2013
    Publication date: December 11, 2014
    Inventors: Michael A. Barker, Dean W. Smith, Edward J. Marquart, Joseph R. Corrado
  • Patent number: 8155819
    Abstract: The effects of IMU gyro and accelerometer bias errors are significantly reduced in accordance with the present teachings by a system or method for commanding an IMU or vehicle through a series of preprogrammed maneuvers. The maneuvers can be designed to minimize the effects of other gyro errors including scale factor errors, nonlinearities, cross coupling/misalignment, and scale factor asymmetries. A sample maneuver is provided which demonstrates performance based on a sequence of roll and yaw maneuvers resulting in zero build up of error at the end of a maneuver cycle period as a result of these errors. Modification of the system involves the addition of control logic to determine the maneuver period, maneuver rate, and vehicle orientation. No additional hardware beyond possible fuel required to perform the maneuver is required.
    Type: Grant
    Filed: August 13, 2007
    Date of Patent: April 10, 2012
    Assignee: Raytheon Company
    Inventor: Michael A. Barker
  • Publication number: 20110172854
    Abstract: The effects of IMU gyro and accelerometer bias errors are significantly reduced in accordance with the present teachings by a system or method for commanding an IMU or vehicle through a series of preprogrammed maneuvers. The maneuvers can be designed to minimize the effects of other gyro errors including scale factor errors, nonlinearities, cross coupling/misalignment, and scale factor asymmetries. A sample maneuver is provided which demonstrates performance based on a sequence of roll and yaw maneuvers resulting in zero build up of error at the end of a maneuver cycle period as a result of these errors. Modification of the system involves the addition of control logic to determine the maneuver period, maneuver rate, and vehicle orientation. No additional hardware beyond possible fuel required to perform the maneuver is required.
    Type: Application
    Filed: August 13, 2007
    Publication date: July 14, 2011
    Inventor: Michael A. Barker