Patents by Inventor Nicholas Albion

Nicholas Albion 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: 20190352003
    Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
    Type: Application
    Filed: July 13, 2019
    Publication date: November 21, 2019
    Inventors: John E. Mercer, Nicholas Albion, Mark Bartel, Marc Feifel, Mark Marvin
  • Patent number: 10464662
    Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: November 5, 2019
    Assignee: Merlin Technology, Inc.
    Inventors: John E. Mercer, Marc Feifel, Mark Marvin, Nicholas Albion
  • Patent number: 10351231
    Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
    Type: Grant
    Filed: August 26, 2017
    Date of Patent: July 16, 2019
    Assignee: Merlin Technology, Inc.
    Inventors: John E. Mercer, Nicholas Albion, Mark Bartel, Marc Feifel, Mark Marvin
  • Publication number: 20180346110
    Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.
    Type: Application
    Filed: August 22, 2018
    Publication date: December 6, 2018
    Inventors: John E. Mercer, Marc Feifel, Mark Marvin, Nicholas Albion
  • Patent number: 5765783
    Abstract: A vertically launchable and recoverable winged aircraft includes an airframe, a least one proprotor connected to the airframe through a rotatable drive shaft, and collective and cyclic pitch control systems. The airframe includes a wing having a leading edge and a trailing edge which define a forward direction of flight in an airplane mode. The proprotors each have an axis of rotation generally parallel to the forward direction of flight in airplane mode, and include at least two proprotor blades. The cyclic pitch control system is operably connected to each blade to control the pitch of each blade, so that the aircraft is capable of controlled helicopter mode flight when the wing leading edge is pointed in a generally upward direction.
    Type: Grant
    Filed: February 26, 1996
    Date of Patent: June 16, 1998
    Assignee: The Boeing Company
    Inventor: Nicholas Albion
  • Patent number: 5424535
    Abstract: A three-phase angular position sensor is described in which three beams of light having polarization directions rotated 60.degree. to each other are passed through a polarizer, the rotational position of the polarizer representing an angle to be measured. The intensities of the beams transmitted through the polarizer uniquely encode its angle over a 180.degree. range. This range may be doubled, for example, by including a binary track. A two-phase angular position sensor is also described in which two beams have polarization directions oriented 45.degree. with respect to one another.
    Type: Grant
    Filed: April 29, 1993
    Date of Patent: June 13, 1995
    Assignee: The Boeing Company
    Inventors: Nicholas Albion, Romeal F. Asmar, Raymond W. Huggins, Glen E. Miller, Charles R. Porter
  • Patent number: D367253
    Type: Grant
    Filed: May 4, 1995
    Date of Patent: February 20, 1996
    Assignee: The Boeing Company
    Inventor: Nicholas Albion