Patents Assigned to Textron
  • Patent number: 11428485
    Abstract: A firearm for firing case-telescoped (CT) rounds includes a barrel configured for transit of a bullet of a live CT cartridge in a live-fire operating mode. The live CT cartridge is chambered and fired from a live-fire chamber installed in the live-fire operating mode. The firearm further includes a blank-fire chamber configured to chamber and fire a blank CT cartridge in a blank-fire operating mode, wherein the blank-fire chamber has a second diameter less than a first diameter of the live-fire chamber, to prevent chambering of the live CT cartridge in the blank-fire operating mode. The arrangement can enhance safety by preventing accidental firing of a live round during operation when it is assumed that only blanks are being fired.
    Type: Grant
    Filed: January 15, 2021
    Date of Patent: August 30, 2022
    Assignee: Textron Systems Corporation
    Inventors: William Henry Engel, IV, David Timothy Horst
  • Patent number: 11427350
    Abstract: A method of forming a rotor blade, including forming at least one of a partial upper skin, a partial lower skin, and a partial support network using an additive manufacturing process; and forming a first receptacle in at least a one of the partial upper skin, the partial lower skin, and the partial support network using the additive manufacturing process. The first receptacle is configured to receive of at least one of an electronic component and a mechanical component. In some embodiments, there is a method of manufacturing a rotor blade that includes forming a first locating receptacle in at least one of the upper skin, the lower skin, and the support network using the additive manufacturing process; and positioning at least one of the upper skin, the lower skin, and the support network in a desired position on a fixture based, in part, on the first locating receptacle.
    Type: Grant
    Filed: January 31, 2019
    Date of Patent: August 30, 2022
    Assignee: Textron Innovations Inc.
    Inventor: Justin A. Rivera
  • Patent number: 11427315
    Abstract: A rotor blade control system and methods therefor including a hub assembly pivotally attached to a rotor blade; a mast attached to the hub assembly; a swashplate assembly engaged with the mast and including a swashplate actuation mechanism pivotally coupled with the non-rotating ring at a plurality of coupling locations for moving the non-rotating ring and pivotally coupled with the base at a plurality of base locations, the swashplate actuation mechanism comprises a plurality of substantially triangular dual actuator assemblies that are independently and concurrently operable to move the respective coupling location so as to impart movement on the non-rotating ring. The swashplate actuation mechanism is configured to move the swashplate assembly about a longitudinal axis and a lateral axis in response to a cyclic input. The swashplate actuation mechanism is configured to move the swashplate assembly along the mast in response to a collective input.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: August 30, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Robert P. Reynolds, Glenn A. Shimek, Brady G. Atkins, William D. Girard
  • Publication number: 20220266997
    Abstract: Embodiments are directed to a tiltrotor aircraft having a wing, a proprotor pivotably mounted on the wing, and a downstop striker attached to the proprotor using a load pin, wherein the load pin is configured to generate an output signal representing a force between the proprotor and the wing. A downstop mounted on the wing is aligned to be in contact with the downstop striker when the proprotor is in a horizontal position. A conversion actuator moves the proprotor between a horizontal position and vertical position. A flight control computer is coupled to the output signal from the load pin and configured to control the conversion actuator, wherein the flight control computer is configured to cause the conversion actuator to increase the force if the force is less than a first selected preload value or to decrease the force if the force is greater than a second selected preload value.
    Type: Application
    Filed: February 24, 2021
    Publication date: August 25, 2022
    Applicant: TEXTRON INNOVATIONS INC.
    Inventors: Evan Butler Bennett, George Ryan Decker, Thomas Earl Johnson
  • Publication number: 20220267005
    Abstract: A fast-rope system for use with a rotary aircraft includes a tubular housing attached to an interior portion of a cabin and adjacent to an upper portion of an exit door opening of the rotary aircraft and a fast-rope frame structure rotatably coupled to the tubular housing. The fast-rope frame structure includes a cylindrical pipe contained partially within the tubular housing and operable to rotate within the tubular housing and a cantilever beam structure fixedly connected to the cylindrical pipe and configured to have a fast rope attached thereto and move in response to rotation of the cylindrical pipe within the tubular housing.
    Type: Application
    Filed: February 24, 2021
    Publication date: August 25, 2022
    Applicant: Bell Textron Inc.
    Inventors: Craig CILLESSEN, Marco BAYERLEIN, Ansgar Hannes BAISCH, Ralf KASSNER
  • Publication number: 20220266962
    Abstract: A seabased resupply system includes a fuel containment structure containing fuel and extending fore and aft along a longitudinal axis, a pump on the fuel containment structure operable to pump the fuel, containers located on an exterior of opposite lateral sides of the fuel containment structure, and an operating system located inside one or more of the containers, the operating system comprising at least one selected from a power supply, a communication system, and a control processor.
    Type: Application
    Filed: April 29, 2022
    Publication date: August 25, 2022
    Applicant: Textron Innovations Inc.
    Inventors: Jeffrey Paul NISSEN, Troy Cyril Schank, Peter Charles ROBICHAUX, Jason Paul HURST, Todd Christopher WORDEN
  • Publication number: 20220267025
    Abstract: A pylon tracking system for a tiltrotor aircraft including first and second pylons each having a pylon conversion actuator with primary and backup drive systems. The pylon tracking system includes a plurality of rotary position sensors including a first rotary position sensor coupled to the primary drive system of the first pylon, a second rotary position sensor coupled to the backup drive system of the first pylon, a third rotary position sensor coupled to the primary drive system of the second pylon and a fourth rotary position sensor coupled to the backup drive system of the second pylon. A flight control computer is in communication with the plurality of rotary position sensors and is configured to process feedback therefrom to identify a differential pylon angle between the first and second pylons during pylon conversion operations.
    Type: Application
    Filed: December 3, 2021
    Publication date: August 25, 2022
    Applicant: Textron Innovations Inc.
    Inventors: Jacob Eugene Augustyn, Evan Butler Bennett, Charles Eric Covington, Thomas Earl Johnson, JR.
  • Patent number: 11420733
    Abstract: An airfoil component assembly for an aircraft includes an additively manufactured flyaway tool including an infill support core and an interface sheet surrounding the infill support core, a spar formed from one or more layers of composite material disposed on the interface sheet of the flyaway tool and a skin formed from one or more layers of composite material disposed on the spar and the interface sheet of the flyaway tool. The flyaway tool, the spar and the skin form the airfoil component assembly for use by the aircraft in flight.
    Type: Grant
    Filed: April 27, 2020
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventor: Robert Patrick Wardlaw
  • Patent number: 11420762
    Abstract: A rotor assembly including a rotor mast, a rotor hub coupled to the rotor mast, a plurality of rotor blades coupled to the rotor hub, a control tube extending through the rotor mast, a crosshead coupled to the control tube, and a mechanism configured to drive the rotor mast in rotation. Wherein the mechanism is longitudinally positioned between a top portion and a bottom portion of the control tube and translation of the control tube relative to the rotor mast causes rotation of the rotor blades about their pitch-change axes. While the crosshead is installed, the crosshead is prevented from angular rotation about the mast axis. A pin of a rotor blade assembly is captured between opposing tabs of the crosshead and movable relative to the opposing tabs in response to translation of the crosshead along the mast axis.
    Type: Grant
    Filed: November 8, 2019
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventors: George Matthew Thompson, Paul Sherrill, Jonathan Knoll
  • Patent number: 11420760
    Abstract: A seal system for coaxially aligned shafts includes an input shaft and an output shaft coaxially aligned with the input shaft. The seal system includes a seal adapter support housing coupled to the output shaft and a seal positioned between an end of the input shaft and an end of the seal adapter support housing. The input shaft is configured to rotate at a speed that is different than a speed of the output shaft.
    Type: Grant
    Filed: June 29, 2020
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Charles Hubert Speller, George Matthew Thompson
  • Patent number: 11420735
    Abstract: A method of reducing noise generated by a tilt-rotor aircraft includes transitioning the tilt-rotor aircraft into an airplane mode from a helicopter mode, and reducing a speed of a plurality of rotor blades of a first pair of rotors of the tilt-rotor aircraft to be less than a speed of a plurality of rotor blades of a second pair of rotors that are positioned forward of and in-line with the first pair of rotors. A flight control system configured to reduce a noise level of a tilt-rotor aircraft includes a flight control computer comprising a processor, a propulsion system communicatively coupled to the flight control computer, a first pair of rotors and a second pair of rotors communicatively coupled with the flight control computer and the propulsion system.
    Type: Grant
    Filed: September 24, 2019
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventor: Royce Wayne Snider
  • Patent number: 11421593
    Abstract: An air intake system for an aircraft engine includes an air duct having an inlet port to provide fluid communication between the inlet port and the engine and a removable air filter assembly configured to interface with the inlet port of the air duct and a skin of the aircraft. The air filter assembly includes an air filter frame having an outer wall and an inner wall, the outer wall of the air filter frame forming an air filter slot. The air filter assembly also includes a bypass door forward of the air filter slot and an air filter insertable into the air filter slot. The bypass door is movable between a closed door position and an open door position, air flowing to the inlet port of the air duct via the air filter in the closed door position and bypassing the air filter in the open door position.
    Type: Grant
    Filed: January 15, 2020
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventor: William Mathisen Gons
  • Patent number: 11420758
    Abstract: A method of reducing noise generated by a tilt-rotor aircraft includes transitioning the tilt-rotor aircraft into an airplane mode from a helicopter mode, and reducing a speed of a first pair of fans of the tilt-rotor aircraft to be less than a speed of a second pair of fans that are positioned in-line with the first pair of fans. A flight control system configured to reduce a noise level of a tilt-rotor aircraft includes a flight control computer comprising a processor, a propulsion system communicatively coupled to the flight control computer, a first pair of fans and a second pair of fans communicatively coupled with the flight control computer and the propulsion system. The processor is operable to implement a method that includes transitioning the tilt-rotor aircraft into an airplane mode from a helicopter mode, and reducing a speed of the first pair of fans to be less than a speed of the second pair of fans that are positioned in-line with the first pair of fans.
    Type: Grant
    Filed: June 14, 2019
    Date of Patent: August 23, 2022
    Assignee: Textron Innovations Inc.
    Inventor: Royce Wayne Snider
  • Patent number: 11424605
    Abstract: According to one implementation of the present disclosure, a method is disclosed. The method includes: detecting, on or proximate to one or more surfaces of an aircraft, a presence of an electric-field above a predetermined threshold; and in response to the detection, activating one or more beam sources to generate an ionized column of charge away from the aircraft.
    Type: Grant
    Filed: April 24, 2020
    Date of Patent: August 23, 2022
    Assignee: TEXTRON INNOVATIONS INC.
    Inventor: Phalgun Madhusudan
  • Publication number: 20220258863
    Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having at least one wing. First and second oppositely disposed booms extend longitudinally from the at least one wing. Forward rotors are coupled to the forward ends of the booms and aft rotors are coupled to the aft ends of the booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the booms, and a forward thrust orientation, wherein the forward rotors are forward of the booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the booms, and a forward thrust orientation, wherein the aft rotors are aft of the booms.
    Type: Application
    Filed: December 8, 2021
    Publication date: August 18, 2022
    Applicant: Textron Innovations Inc.
    Inventor: Kip Gregory Campbell
  • Publication number: 20220258851
    Abstract: A method for reducing form drag on a tailsitter aircraft during at least one of takeoff or landing includes vertically taking off from the ground in a tailsitter orientation. The method also includes determining an actual pitch of the tail sitter aircraft in the tailsitter orientation. The method also includes determining a difference between the actual pitch and a predetermined pitch. The method also includes adjusting a heading of the tailsitter aircraft based on the difference to minimize a pitch angle to reduce the form drag on the tailsitter aircraft.
    Type: Application
    Filed: February 12, 2021
    Publication date: August 18, 2022
    Applicant: Bell Textron Inc.
    Inventors: John R. Wittmaak, Jr., Russell C. Peters, Nathaniel G. Lundie
  • Publication number: 20220258873
    Abstract: A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.
    Type: Application
    Filed: February 12, 2021
    Publication date: August 18, 2022
    Applicant: Bell Textron Inc.
    Inventors: Guy Bernard, Jeffrey Epp, William K. Heironimus
  • Patent number: 11415162
    Abstract: A method of fastening gearbox housing components together, comprising: selecting a gearbox housing fastener comprising a straight shaft having a longitudinal axis, a first threaded portion, a single cylindrical central portion, and a second threaded portion, wherein the first and second threaded portions are separated by the cylindrical portion, wherein the cylindrical portion comprises a single reduced diameter that is less than first and second minor diameters of the first and second threaded portions, the first and second threaded portions are chamfered, and the fastener comprises a material having a tensile strength along the longitudinal axis that is greater than a sheer strength at the cylindrical portion; and fastening the gearbox housing components together with the fastener, wherein the first and third gearbox housing components are fastened with the first and second threaded portions, and the second gearbox housing component is positioned around the single cylindrical central portion.
    Type: Grant
    Filed: September 30, 2021
    Date of Patent: August 16, 2022
    Assignee: TEXTRON INNOVATIONS INC.
    Inventor: Scott David Poster
  • Patent number: 11415174
    Abstract: Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.
    Type: Grant
    Filed: April 11, 2019
    Date of Patent: August 16, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Tyler Wayne Baldwin, Kyle Thomas Cravener, Tyson Henry
  • Patent number: 11414183
    Abstract: In an implementation, the compound helicopter may include at least one rotary wing system, at least one first power generator and at least one second power generator. The at least one first power generator may rotate the at least one rotary wing blade to provide lift and a primary thrust force in a first direction to the helicopter. The at least one second power generator may be connected to the helicopter and may provide lift and a secondary thrust force in a direction that is independent of a direction of the primary thrust force and may also provide a secondary thrust force in a direction that is substantially parallel to the primary thrust force.
    Type: Grant
    Filed: August 14, 2019
    Date of Patent: August 16, 2022
    Assignee: TEXTRON INNOVATIONS INC.
    Inventors: Jouyoung Jason Choi, Carlos Alexandra Fenny