Patents Assigned to Textronics, Inc.
  • Publication number: 20200070967
    Abstract: Embodiments are directed to systems and methods for providing a control link for an aircraft in which the control link comprises an impact-resistant structure with a redundant load path. The control link has an inner structure that is sized to carry the anticipated load of the flight control system and to meet all safety factors. The control link also has an outer structure that is sacrificial and configured to absorb impact damage during operation, thereby protecting the inner structure. The outer structure is also designed to carry the anticipated load of the flight control system on its own, independent of the inner structure, and to meet all safety factors. If the outer structure fails, the inner structure allows for continued safe operation of the flight control system. The space or cavity between the inner and outer structures may be filled with a material, such as a closed-cell foam, to improve the impact resistance of the outer structure.
    Type: Application
    Filed: August 30, 2018
    Publication date: March 5, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: John Benjamin Osborne, Ramesh Thiagarajan, Charles Joseph Kilmain
  • Publication number: 20200070994
    Abstract: Embodiments are directed to systems and methods for reducing the infrared signature of a vehicle, specifically to the use of mixed flow or centrifugal blowers to reduce the amount of infrared radiation being emitted from the engine exhaust. A blower and mixer are used to cool the exhaust gas from an aircraft engine. The blower and mixer use a tertiary exhaust duct to swirl cool air from an engine particle separator (EPS) and/or oil cooler, for example, with the hot engine exhaust gas. Existing blowers in the EPS or oil cooler may be used to motivate air flow so that a unique or dedicated blower is not required. In addition to reducing exposure to hostile forces, other benefits of cooling the exhaust gas include greatly reduced ground-impingement temperatures and safer personnel working zones because the hot plume is mostly eliminated.
    Type: Application
    Filed: August 30, 2018
    Publication date: March 5, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Angel D. Rosado, William Gons
  • Publication number: 20200073412
    Abstract: In one embodiment, a method is performed by a computer system in an aircraft. The method includes receiving an advance indication of a take-off or landing event to be executed by the aircraft in proximity to a landing area such that the landing area includes an arrangement of a plurality of emitters of electromagnetic radiation. The method further includes, responsive to the receiving, detecting, via a sensor in communication with the computer system, emission states of at least some of the plurality of emitters. In addition, the method includes transforming the detected emission states into an instruction set for the take-off or landing event. The method also includes initiating monitoring of the aircraft relative to the instruction set as the aircraft executes the take-off or landing event in proximity to the landing area.
    Type: Application
    Filed: September 4, 2018
    Publication date: March 5, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Michael Kevin MCNAIR, Andrew Vincent LOUIS
  • Patent number: 10578207
    Abstract: One aspect of a cooling system includes a gas source connected to a component to be cooled. The gas source continuously supplies compressed gas to the component in response to an input. The cooling system also includes a controller connected to the gas source, the controller to provide the input to the gas source to continuously supply the compressed gas to the component.
    Type: Grant
    Filed: July 24, 2014
    Date of Patent: March 3, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brian S. Modrzejewski, Monte McGlaun, Travis Jurell
  • Patent number: 10577079
    Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: March 3, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Jared Mark Paulson, Tyler Wayne Baldwin, Kyle Thomas Cravener
  • Publication number: 20200062384
    Abstract: An aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween forming a central region. A two-dimensional distributed thrust array and a flight control system are coupled to the airframe. A nose cone and an afterbody are each selectively coupled to the airframe. In a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe such that the nose cone and the afterbody each extend between the first and second wings and between first and second pylons to form a cargo enclosure with an aerodynamic outer shape. In a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during flight.
    Type: Application
    Filed: May 30, 2019
    Publication date: February 27, 2020
    Applicant: Bell Textron Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd, Glenn Edward Isbell, JR., Matthew John Hill
  • Publication number: 20200062382
    Abstract: A tiltrotor aircraft having a propulsion configuration that divorces the engine core power from the thrust fan, using a combined gearbox with a plurality of clutches to couple and decouple one or more rotor systems and one or more thrust fans. The aircraft can be operable for vertical takeoff and landing (VTOL) in a helicopter mode, forward flight in a proprotor mode, and high-speed forward flight in an airplane (jet) mode. The propulsion configuration provides shaft horsepower (SHP) to rotors for VTOL flight, while also providing SHP to the thrust fan for high speed flight. Allowing the rotor and the thrust fan to be clutched on and off, sequentially, enables transition from rotor-borne VTOL flight to wing-borne thrust fan flight, and back.
    Type: Application
    Filed: September 26, 2018
    Publication date: February 27, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventor: Troy C. Schank
  • Patent number: 10574066
    Abstract: In one embodiment, an aircraft electronics system includes a hardware processor, a charge collection circuit to collect charge; a switching circuit controlled by the hardware processor to discharge the charge collected on the charge collection circuit through a bonding circuit formed from a chassis and a bonding surface; and a voltage measurement circuit to measure a voltage difference between measurement terminals across the chassis and the bonding surface.
    Type: Grant
    Filed: December 4, 2017
    Date of Patent: February 25, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Gary S. Froman
  • Patent number: 10569867
    Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: February 25, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Andrew Maresh, Frank Bradley Stamps, Patrick Ryan Tisdale, Robert Patrick Wardlaw, Andrew Haldeman, Drew Alan Sutton
  • Patent number: 10569869
    Abstract: A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: February 25, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Jared Mark Paulson, Tyler Wayne Baldwin, Kyle Thomas Cravener
  • Patent number: 10569866
    Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.
    Type: Grant
    Filed: July 2, 2018
    Date of Patent: February 25, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kyle Thomas Cravener, Paul Sherrill
  • Publication number: 20200056696
    Abstract: An aircraft includes a variable-speed gearbox. The variable-speed gearbox includes a low-speed gear train and a high-speed gear train, each gear train of which is configured to selectively provide torque from an engine of the aircraft to a proprotor. The variable-speed gearbox also includes a hydraulic system configured to provide torque to the proprotor. The hydraulic system includes a hydraulic pump driven by the engine of the tiltrotor aircraft and a variable-displacement motor driven by a hydraulic fluid from the hydraulic pump.
    Type: Application
    Filed: August 20, 2018
    Publication date: February 20, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Carlos Alexander Fenny, Frank Stamps
  • Publication number: 20200055586
    Abstract: Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
    Type: Application
    Filed: August 20, 2018
    Publication date: February 20, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Christopher Edward Foskey, Michael Christopher Burnett
  • Publication number: 20200055593
    Abstract: A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.
    Type: Application
    Filed: July 23, 2018
    Publication date: February 20, 2020
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Troy Schank, Frank B. Stamps
  • Publication number: 20200055410
    Abstract: An exemplary method includes controlling a rotation rate of a rotor in a vehicle, detecting that an electric motor system is electrically energized and rotating the rotor at least at a minimum rotation rate that is greater than zero in response to the electric motor system being electrically energized. The rotor may be rotated at least at the minimum rotation rate when the electric motor system is energized and the motor is turned-off.
    Type: Application
    Filed: August 14, 2018
    Publication date: February 20, 2020
    Applicant: Bell Helicpter Textron Inc.
    Inventor: Eric Albert Sinusas
  • Patent number: 10562617
    Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
    Type: Grant
    Filed: November 13, 2016
    Date of Patent: February 18, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Jouyoung Jason Choi, David Heverly, Michael Seifert, Michael Smith, Frank Brad Stamps, Thomas Parham, Jr., Amarjit Olenchery Kizhakkepat
  • Patent number: 10562618
    Abstract: A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: February 18, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Daniel Bryan Robertson, Kirk Landon Groninga
  • Patent number: 10562202
    Abstract: A method of cutting a wafer of composite core from a bulk composite core includes stabilizing the bulk composite core with a fixture, the bulk composite core having a plurality of tube members. The method also includes cutting through each of the tube members to create the wafer while the bulk composite core is stabilized by the fixture.
    Type: Grant
    Filed: February 15, 2018
    Date of Patent: February 18, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Phillip A. Kendrick, Levi H. Armstrong
  • Publication number: 20200047898
    Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.
    Type: Application
    Filed: August 9, 2018
    Publication date: February 13, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventor: Eric Albert SINUSAS
  • Publication number: 20200047911
    Abstract: Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.
    Type: Application
    Filed: August 9, 2018
    Publication date: February 13, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventor: Thomas Dewey Parsons