Patents by Inventor Erik Harrington
Erik Harrington 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: 11111005Abstract: A secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.Type: GrantFiled: November 22, 2017Date of Patent: September 7, 2021Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Erik Harrington, Timothy Michael Mayer
-
Patent number: 10934017Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes performing real-time monitoring of torque generated for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft, generating RHS and LHS torque information from results of the monitoring and comparing the RHS and LHS torque information at least with each other or with corresponding historic torque information.Type: GrantFiled: September 25, 2017Date of Patent: March 2, 2021Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Erik Harrington, Christian Miller, Yuniya S. Bishop
-
Patent number: 10800542Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.Type: GrantFiled: July 14, 2017Date of Patent: October 13, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Erik Harrington, Andrew N. Baines
-
Patent number: 10753893Abstract: A health monitoring system provided with an aircraft includes a temperature sensor assembly and a control system. The temperature sensor assembly is disposed within a housing and is positioned to monitor at least one of a temperature and a temperature rise of a gear of an actuator that is positioned within the housing. The control system is in communication with the temperature sensor. The control system is configured to output for display an indicator responsive to at least one of the temperature and the temperature rise of the gear being greater than a threshold.Type: GrantFiled: January 26, 2018Date of Patent: August 25, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Erik Harrington, Bahram Z. Movahed
-
Patent number: 10730610Abstract: An aircraft is provided. The aircraft includes fuselage, an aerodynamic element extending from the fuselage and including a main section and an adjustable section which is adjustable relative to the main section, a power distribution unit (PDU) configured to generate torque to drive an adjustment of the adjustable section, an actuator, torque tubes and elastomeric couplings. The PDU is disposed proximate to a fuselage-aerodynamic interface. The actuator is disposed along the aerodynamic element and is receptive of the torque for driving the adjustment of the adjustable section. The torque tubes transmit the torque from the PDU to the actuator and are arranged between the PDU and the actuator such that adjacent torque tubes define an obtuse angle. The elastomeric couplings are disposed at respective ends of each of the torque tubes to enable torque transmission between at least the adjacent torque tubes defining the obtuse angle.Type: GrantFiled: April 20, 2017Date of Patent: August 4, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Erik Harrington, Yuniya S. Bishop, Christian Miller
-
Patent number: 10703462Abstract: A method for braking a motor in a high lift system of an aircraft, the high lift system comprising a central power drive unit for moving high lift surfaces arranged at a wing through providing rotational power by means of a transmission shaft to a plurality of drive stations operably coupled with the high lift surfaces; which power drive unit is operatively coupled to a controller and comprises at least one electric motor coupled therewith. The method includes determining a braking requirement for the at least one electric motor, measuring at least one of a current command to the motor and a current speed and direction of the at least one electric motor, based on the braking requirement, applying a braking command to the at least one electric motor, and reducing the braking command as the at least one electric motor comes to rest.Type: GrantFiled: August 25, 2017Date of Patent: July 7, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Erik Harrington, Victor Barger, Adam M. Finney, Timothy Michael Mayer, Yuniya S. Bishop, Adam Crandall, Darrell E. Ankney, Eugene W. Dolfi, Michael C. Harke, Christian Miller, Artemio Pérez
-
Patent number: 10696380Abstract: Control surface operating systems for controlling aerodynamic control surfaces of aircraft are provided. The systems includes a drive system operably connected to a drive shaft, the drive system including a continuously variable transmission, at least one actuator operably connected to the drive shaft and arranged to convert rotational movement of the drive shaft to move at least a portion of the aerodynamic control surface, and at least one control surface operably connected to the at least one actuator, wherein the at least one control surface is adjusted by the at least one actuator.Type: GrantFiled: July 20, 2017Date of Patent: June 30, 2020Assignee: HAMILTON SUNSTRAND CORPORATIONInventors: Christian Miller, Yuniya S. Bishop, Erik Harrington
-
Patent number: 10589871Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes generating torque for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft in a power drive unit (PDU) based on torque-limiter (TL) thresholds, performing real-time monitoring of the torque at the RHS and LHS of the aircraft, generating RHS and LHS torque information from results of the performing of the real-time monitoring, analyzing the RHS and LHS torque information and controlling operations of the PDU based on results of the analysis by at least one of modifying, tuning and defining the TL thresholds.Type: GrantFiled: September 29, 2017Date of Patent: March 17, 2020Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Erik Harrington, Christian Miller, Yuniya S. Bishop, Jason B. Kreienheder, Michael Skirtich, Gregory T. Wallen
-
Patent number: 10501201Abstract: Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.Type: GrantFiled: March 27, 2017Date of Patent: December 10, 2019Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Erik Harrington, Christian Miller, Yuniya S. Bishop
-
Patent number: 10473163Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.Type: GrantFiled: August 22, 2017Date of Patent: November 12, 2019Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Erik Harrington, David G. Hill, Rachel Gallagher, Cory M. Crandall-Seibert, Victor Barger, Timothy Michael Mayer, Artemio Pérez, Christian Miller, Yuniya S. Bishop
-
Publication number: 20190234892Abstract: A health monitoring system provided with an aircraft includes a temperature sensor assembly and a control system. The temperature sensor assembly is disposed within a housing and is positioned to monitor at least one of a temperature and a temperature rise of a gear of an actuator that is positioned within the housing. The control system is in communication with the temperature sensor. The control system is configured to output for display an indicator responsive to at least one of the temperature and the temperature rise of the gear being greater than a threshold.Type: ApplicationFiled: January 26, 2018Publication date: August 1, 2019Inventors: Erik Harrington, Bahram Z. Movahed
-
Publication number: 20190152583Abstract: A secondary flight control system is provided. The secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.Type: ApplicationFiled: November 22, 2017Publication date: May 23, 2019Inventors: Erik Harrington, Timothy Michael Mayer
-
Publication number: 20190092492Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes performing real-time monitoring of torque generated for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft, generating RHS and LHS torque information from results of the monitoring and comparing the RHS and LHS torque information at least with each other or with corresponding historic torque information.Type: ApplicationFiled: September 25, 2017Publication date: March 28, 2019Inventors: Erik Harrington, Christian Miller, Yuniya S. Bishop
-
Publication number: 20190092491Abstract: A method of prognostic health monitoring is provided for use with an aircraft. The method includes generating torque for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft in a power drive unit (PDU) based on torque-limiter (TL) thresholds, performing real-time monitoring of the torque at the RHS and LHS of the aircraft, generating RHS and LHS torque information from results of the performing of the real-time monitoring, analyzing the RHS and LHS torque information and controlling operations of the PDU based on results of the analysis by at least one of modifying, tuning and defining the TL thresholds.Type: ApplicationFiled: September 29, 2017Publication date: March 28, 2019Inventors: Erik Harrington, Christian Miller, Yuniya S. Bishop, Jason B. Kreienheder, Michael Skirtich, Gregory T. Wallen
-
Publication number: 20190063508Abstract: A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.Type: ApplicationFiled: August 22, 2017Publication date: February 28, 2019Inventors: Erik Harrington, David G. Hill, Rachel Gallagher, Cory M. Crandall-Seibert, Victor Barger, Timothy Michael Mayer, Artemio Pérez, Christian Miller, Yuniya S. Bishop
-
Publication number: 20190061531Abstract: A method for braking a motor in a high lift system of an aircraft, the high lift system comprising a central power drive unit for moving high lift surfaces arranged at a wing through providing rotational power by means of a transmission shaft to a plurality of drive stations operably coupled with the high lift surfaces; which power drive unit is operatively coupled to a controller and comprises at least one electric motor coupled therewith. The method includes determining a braking requirement for the at least one electric motor, measuring at least one of a current command to the motor and a current speed and direction of the at least one electric motor, based on the braking requirement, applying a braking command to the at least one electric motor, and reducing the braking command as the at least one electric motor comes to rest.Type: ApplicationFiled: August 25, 2017Publication date: February 28, 2019Inventors: Erik Harrington, Victor Barger, Adam M. Finney, Timothy Michael Mayer, Yuniya S. Bishop, Adam Crandall, Darrell E. Ankney, Eugene W. Dolfi, Michael C. Harke, Christian Miller, Artemio Pérez
-
Publication number: 20190023378Abstract: Control surface operating systems for controlling aerodynamic control surfaces of aircraft are provided. The systems includes a drive system operably connected to a drive shaft, the drive system including a continuously variable transmission, at least one actuator operably connected to the drive shaft and arranged to convert rotational movement of the drive shaft to move at least a portion of the aerodynamic control surface, and at least one control surface operably connected to the at least one actuator, wherein the at least one control surface is adjusted by the at least one actuator.Type: ApplicationFiled: July 20, 2017Publication date: January 24, 2019Inventors: Christian Miller, Yuniya S. Bishop, Erik Harrington
-
Publication number: 20190017492Abstract: A ram air turbine (RAT) is provided and includes a turbine assembly including blades and a hub to which the blades are connected, a generator or a pump and a drivetrain mechanically interposed between the turbine assembly and the generator or the pump. Each blade includes an exterior, airfoil-shaped structure defining an interior and support structures disposed within the interior which connect with an inner surface of the exterior, airfoil-shaped structure and which define hollow regions within the interior.Type: ApplicationFiled: July 14, 2017Publication date: January 17, 2019Inventors: Erik Harrington, Andrew N. Baines
-
Publication number: 20180304995Abstract: An aircraft is provided. The aircraft includes fuselage, an aerodynamic element extending from the fuselage and including a main section and an adjustable section which is adjustable relative to the main section, a power distribution unit (PDU) configured to generate torque to drive an adjustment of the adjustable section, an actuator, torque tubes and elastomeric couplings. The PDU is disposed proximate to a fuselage-aerodynamic interface. The actuator is disposed along the aerodynamic element and is receptive of the torque for driving the adjustment of the adjustable section. The torque tubes transmit the torque from the PDU to the actuator and are arranged between the PDU and the actuator such that adjacent torque tubes define an obtuse angle. The elastomeric couplings are disposed at respective ends of each of the torque tubes to enable torque transmission between at least the adjacent torque tubes defining the obtuse angle.Type: ApplicationFiled: April 20, 2017Publication date: October 25, 2018Inventors: Erik Harrington, Yuniya S. Bishop, Christian Miller
-
Patent number: 10086924Abstract: A selector lever includes a detent pin that travels along a shaft for being positioned within a detent slot of a detent plate for securing the selector lever in place. A magnetic detent pin alignment mechanism provides feedback to an operator for assisting in maneuvering the selector lever to a predetermined position wherein the detent pin may be positioned within a desired detent slot.Type: GrantFiled: April 29, 2016Date of Patent: October 2, 2018Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Cory M. Crandall-Seibert, Erik Harrington, Jeffrey Paul Jacobs