Patents by Inventor Kynn J. Schulte

Kynn J. Schulte 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: 20210362837
    Abstract: Embodiments are directed to a blade lock comprising a fold lock adapted to prevent folding of a rotor blade in a fold-lock position and to allow folding of the rotor blade in a pitch-lock position. The blade lock further comprises a pitch lock adapted to allow pitch movement of a rotor blade in a fold-lock position and to prevent pitch movement of the rotor blade in the pitch-lock position. A spring-loaded link pivotally connects both the fold lock and the pitch lock and is adapted to provide passive, overcenter locking in the fold-lock position. An actuator is coupled to the pitch lock and is adapted to move the pitch lock and the fold lock between the fold-lock and pitch-lock positions.
    Type: Application
    Filed: May 20, 2020
    Publication date: November 25, 2021
    Applicant: Bell Textron Inc.
    Inventors: Kyle Thomas Cravener, Andrew Ryan Maresh, Brady Garrett Atkins, Kynn J. Schulte, Troy Schank
  • Patent number: 9218002
    Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.
    Type: Grant
    Filed: February 7, 2011
    Date of Patent: December 22, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Kynn J. Schulte, Robert L. Fortenbaugh, Kenneth E. Builta
  • Publication number: 20130030607
    Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.
    Type: Application
    Filed: February 7, 2011
    Publication date: January 31, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Kynn J. Schulte, Robert L. Fortenbaugh, Kenneth E. Builta
  • Patent number: 8108085
    Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.
    Type: Grant
    Filed: May 18, 2011
    Date of Patent: January 31, 2012
    Assignee: Textron Innovations Inc.
    Inventors: Kenneth E. Builta, James E. Harris, Bryan P. Honza, Jeffrey W. Epp, Kynn J. Schulte
  • Publication number: 20110270474
    Abstract: A system for controlling flight of an aircraft has sensors, a receiver, and a digital control system, all of which are carried aboard the aircraft. The sensors determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver receives transmitted data communicating the position and movement of a reference vehicle relative to the earth. The control system calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors and the receiver and then commands flight control devices on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.
    Type: Application
    Filed: May 18, 2011
    Publication date: November 3, 2011
    Inventors: Kenneth E. Builta, James E. Harris, Bryan P. Honza, Jeffrey W. Epp, Kynn J. Schulte
  • Patent number: 8014909
    Abstract: A system for controlling flight of an aircraft has sensors (37, 43), a receiver (45), and a digital control system (57), all of which are carried aboard the aircraft. The sensors (37, 43) determine the position of the aircraft relative to the earth and the inertial movement of the aircraft. The receiver (45) receives transmitted data (51, 55) communicating the position and movement of a reference vehicle relative to the earth. The control system (57) calculates the position and velocity of the aircraft relative to the reference vehicle using the data from the sensors (37, 43) and the receiver (45) and then commands flight control devices (33) on the aircraft for maneuvering the aircraft in a manner that maintains a selected position and/or velocity relative to the reference vehicle. The system allows use of a graphical or tactile user interfaces.
    Type: Grant
    Filed: March 25, 2004
    Date of Patent: September 6, 2011
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kenneth E. Builta, James E. Harris, Bryan P. Honza, Jeffrey W. Epp, Kynn J. Schulte
  • Patent number: 7931238
    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
    Type: Grant
    Filed: September 12, 2005
    Date of Patent: April 26, 2011
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kenneth E. Builta, Kynn J. Schulte
  • Patent number: 7571879
    Abstract: One embodiment of the present invention is a method for automatically controlling the conversion of a tiltrotor aircraft. An airspeed command for the tiltrotor aircraft is received. The airspeed command is converted to a pylon position. A difference between the airspeed command and a measured airspeed is calculated. The difference between the airspeed command and a measured airspeed is converted to a dynamic pylon position. A total pylon position is calculated from the pylon position and the dynamic pylon position. A pylon of the tiltrotor aircraft is moved to the total pylon position. Another embodiment of the present invention is a system for calculating a position of a pylon of a tiltrotor aircraft based on an airspeed command. The system includes an airspeed command module, a pylon trim position module, a dynamic pylon position module, and a pylon position module.
    Type: Grant
    Filed: September 22, 2006
    Date of Patent: August 11, 2009
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kenneth E. Builta, Kynn J. Schulte, James E. Harris, Billy K. Gore
  • Publication number: 20090114764
    Abstract: One embodiment of the present invention is a method for automatically controlling the conversion of a tiltrotor aircraft. An airspeed command for the tiltrotor aircraft is received. The airspeed command is converted to a pylon position. A difference between the airspeed command and a measured airspeed is calculated. The difference between the airspeed command and a measured airspeed is converted to a dynamic pylon position. A total pylon position is calculated from the pylon position and the dynamic pylon position. A pylon of the tiltrotor aircraft is moved to the total pylon position. Another embodiment of the present invention is a system for calculating a position of a pylon of a tiltrotor aircraft based on an airspeed command. The system includes an airspeed command module, a pylon trim position module, a dynamic pylon position module, and a pylon position module.
    Type: Application
    Filed: September 22, 2006
    Publication date: May 7, 2009
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Kenneth E. Builta, Kynn J. Schulte, James E. Harris, Billy K. Gore
  • Publication number: 20080308682
    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
    Type: Application
    Filed: September 12, 2005
    Publication date: December 18, 2008
    Inventors: Kenneth E. Builta, Kynn J. Schulte