Patents by Inventor Michael David TRANTHAM
Michael David TRANTHAM 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: 11708155Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.Type: GrantFiled: November 1, 2021Date of Patent: July 25, 2023Assignee: Textron Innovations Inc.Inventors: Douglas Andrew Goodwin, David Andrew Prater, Eric Stephen Olson, David Bryan Roberts, Chia-Wei Su, Michael David Trantham, Charles Eric Covington
-
Patent number: 11604059Abstract: A rotorcraft comprising a rotor blade designed to flap about a hinge point, a measurement system designed to measure blade flapping, and a processing system designed to alter blade flapping measurements. The processing system further comprises a correction process to alter a blade flapping measurement dependent on rotor RPM or rotor torque.Type: GrantFiled: June 29, 2020Date of Patent: March 14, 2023Assignee: Textron Innovations Inc.Inventors: Charles Eric Covington, Randall Lee Johnson, Hunter Barton Nelson, Michael David Trantham
-
Patent number: 11505309Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.Type: GrantFiled: May 11, 2021Date of Patent: November 22, 2022Assignee: Textron Innovations Inc.Inventors: Brady Garrett Atkins, Michael David Trantham, Paul David Ruckel
-
Publication number: 20220219810Abstract: In an embodiment, an aircraft includes a pilot input device, a position sensor coupled to the pilot input device, a flight condition sensor and a flight control computer (FCC). The FCC includes a first microprocessor and a second microprocessor. The first microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a first output. The second microprocessor is configured to receive input data from the position sensor and the condition sensor and determine therefrom a second output. The FCC is configured to compare the first output and the second output to yield resultant data. Responsive to a determination that the first output and the second output do not match, the FCC is configured to execute first remediation logic if the resultant data satisfies first error criteria and to execute second remediation logic if the resultant data satisfies second error criteria.Type: ApplicationFiled: January 11, 2021Publication date: July 14, 2022Applicant: Bell Textron Inc.Inventors: Clifton L. HARRELL, Charles Eric COVINGTON, David A. ADJEI, Kevin Matthew TRENDEL, Michael David TRANTHAM, Randall JOHNSON
-
Publication number: 20220212783Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.Type: ApplicationFiled: November 1, 2021Publication date: July 7, 2022Applicant: Textron Innovations Inc.Inventors: Douglas Andrew Goodwin, David Andrew Prater, Eric Stephen Olson, David Bryan Roberts, Chia-Wei Su, Michael David Trantham, Charles Eric Covington
-
Publication number: 20210403147Abstract: A rotorcraft comprising a rotor blade designed to flap about a hinge point, a measurement system designed to measure blade flapping, and a processing system designed to alter blade flapping measurements. The processing system further comprises a correction process to alter a blade flapping measurement dependent on rotor RPM or rotor torque.Type: ApplicationFiled: June 29, 2020Publication date: December 30, 2021Applicant: Bell Textron Inc.Inventors: Charles Eric COVINGTON, Randall Lee JOHNSON, Hunter Barton NELSON, Michael David TRANTHAM
-
Patent number: 11174015Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.Type: GrantFiled: October 5, 2020Date of Patent: November 16, 2021Assignee: Textron Innovations Inc.Inventors: Douglas Andrew Goodwin, David Andrew Prater, Eric Stephen Olson, David Bryan Roberts, Chia-Wei Su, Michael David Trantham, Charles Eric Covington
-
Publication number: 20210261237Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.Type: ApplicationFiled: May 11, 2021Publication date: August 26, 2021Applicant: Bell Textron Inc.Inventors: Brady Garrett ATKINS, Michael David TRANTHAM, Paul David RUCKEL
-
Patent number: 11027821Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.Type: GrantFiled: January 22, 2018Date of Patent: June 8, 2021Assignee: Bell Helicopter Textron Inc.Inventors: Brady Garrett Atkins, Michael David Trantham, Paul David Ruckel
-
Publication number: 20210070430Abstract: A multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly shifts the bypass assembly between engaged and disengaged positions. An engagement status sensor is configured to determine the engagement status of the bypass assembly. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.Type: ApplicationFiled: October 5, 2020Publication date: March 11, 2021Applicant: Bell Textron Inc.Inventors: Douglas Andrew Goodwin, David Andrew Prater, Eric Stephen Olson, David Bryan Roberts, Chia-Wei Su, Michael David Trantham, Charles Eric Covington
-
Publication number: 20200292410Abstract: An example of a rotor-state determining method for a rotor system includes, by a flight control computer, collecting data from a first sensor positioned on a first component of the rotorcraft, wherein the first sensor is isolated from movement of a rotor blade, collecting data from a second sensor positioned on a second component of the rotor system, wherein the second sensor detects movement of the rotor blade, filtering the data collected by the first sensor to remove noise from the data collected by the first sensor, filtering the data collected by the second sensor to remove noise from the data collected by the second sensor, calculating a difference between the filtered first data and the filtered second data to determine a parameter of the rotor blade, and responsive to the motion of the rotor blade, taking a corrective action.Type: ApplicationFiled: November 8, 2019Publication date: September 17, 2020Applicant: Bell Textron Inc.Inventors: Charles Eric COVINGTON, Michael David TRANTHAM, Evan Butler BENNETT
-
Publication number: 20190225322Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.Type: ApplicationFiled: January 22, 2018Publication date: July 25, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Brady Garrett ATKINS, Michael David TRANTHAM, Paul David RUCKEL