Patents Assigned to Textronics, Inc.
  • THERMOSTATICALLY CONTROLLED EMERGENCY LUBRICATION SYSTEM
    Publication number: 20210116016
    Abstract: A lubrication system includes a primary lubrication system for a gearbox of the aircraft, the primary lubrication system comprising a first lubricant tank, and an emergency lubrication system for the gearbox. The emergency lubrication system includes a second lubricant tank coupled to a gearbox of an aircraft, a passive thermostat coupled between the second lubricant tank and the gearbox via a lubricant line, a conductor coupled between the passive thermostat and the gearbox and configured to conduct heat from the gearbox to the passive thermostat, and wherein the passive thermostat is configured to open in response to the conductor being exposed to a temperature that exceeds a threshold temperature.
    Type: Application
    Filed: October 18, 2019
    Publication date: April 22, 2021
    Applicant: Bell Textron Inc.
    Inventor: Douglas Robert MUELLER
  • Aircraft with Rotating Ducted Fan
    Publication number: 20210114720
    Abstract: An aircraft includes a fuselage, and a wing extending from the fuselage along a spanwise axis. A section of the wing is rotatable about the spanwise axis. A ducted fan is mounted to the section of the wing. The ducted fan has a hub configured to be drivingly engaged by an engine. The hub is rotatable about a fan axis. Blades protrude from the hub between roots mounted to the hub and tips radially spaced from the hub. A duct circumferentially extends about the fan axis and is mounted to the tips of the blades to rotate with the blades about the fan axis. The section of the wing and the ducted fan are rotatable about the spanwise axis between a hover mode in which the fan axis is substantially perpendicular to a ground, and an aircraft mode in which the fan axis is substantially parallel to the ground.
    Type: Application
    Filed: October 22, 2019
    Publication date: April 22, 2021
    Applicant: Bell Textron Inc.
    Inventors: Martin LANDRY, Mathieu BELAND, Maxime LAPALME
  • Rotor span-balance pocket
    Patent number: 10981647
    Abstract: The present invention includes a rotor-blade span-balancing system, including a span-balance pocket in a surface of a rotor blade; a cover operably configured to cover the span-balance pocket, wherein the cover is operably configured to be substantially flush with the surface of the rotor blade surface when covering the span-balance pocket, and wherein the cover includes a cover boss for reacting centrifugal force of the cover into the rotor blade; and one or more span-balance weights attached to the cover to span-balance the rotor blade.
    Type: Grant
    Filed: August 2, 2017
    Date of Patent: April 20, 2021
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Robert Self, Nathan P. Green, John R. McCullough, Russell Cole, Paul Sherrill, Robert Wardlaw
  • OVER-CENTERING BLADE LOCK
    Publication number: 20210107638
    Abstract: An exemplary blade lock for a tiltrotor aircraft to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade assembly includes a link pivotally connected to a lever and a bellcrank, where the link is in a center position when the lever is in a locked position disabling the folding degree of freedom and the lever is secured in the locked position when the link is positioned in an over-center position.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Applicant: Bell Textron Inc.
    Inventors: Kyle Thomas CRAVENER, Andrew MARESH
  • Integral Multistage Ring Gear Systems for Aircraft
    Publication number: 20210107671
    Abstract: A drivetrain for an aircraft includes an engine, a driveshaft to receive rotational energy from the engine and a gearbox including a multistage planetary gear system to receive rotational energy from the driveshaft. The multistage planetary gear system includes an integral multistage ring gear system having flanged and cantilevered ends. The integral multistage ring gear system forms a first stage ring gear at the cantilevered end and a second stage ring gear interposed between the flanged end and the first stage ring gear. The multistage planetary gear system includes a first stage sun gear, first stage planet gears and a first stage carrier. The first stage planet gears mate with the first stage ring gear. The multistage planetary gear system includes a second stage sun gear, second stage planet gears and a second stage carrier. The second stage planet gears mate with the second stage ring gear.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Applicant: Bell Textron Inc.
    Inventors: Colton James Gilliland, Russell Lee Mueller, Tyson T. Henry
  • ACTIVE HORIZONTAL STABILIZER FOR HIGH SPEED ROTORCRAFT
    Publication number: 20210107625
    Abstract: A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.
    Type: Application
    Filed: October 13, 2020
    Publication date: April 15, 2021
    Applicant: Bell Textron Inc.
    Inventors: Luke Dafydd Gillett, James Rigsby, Jeffrey Kirkman, Craig Lovell, Andrew Carter, Aaron Alexander Acee
  • SPRING-LOADED LINK
    Publication number: 20210107624
    Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Applicant: Bell Textron Inc.
    Inventors: Kyle Thomas CRAVENER, Christopher Edward FOSKEY, Andrew MARESH
  • Single Butt Line Keel and Roof Beam
    Publication number: 20210107618
    Abstract: Embodiments are directed to an aircraft fuselage comprises two keel beams and two roof beams. Each keel beam is formed as a single component having no joints. Each keel beam comprises a first portion that is configured to define a floor of an aircraft and a second portion that is configured to define a tail section of an aircraft. The second portion is positioned at an angle relative to the first portion. Each roof beam is coupled to the second portion of a corresponding keel beam at a point remote from the first portion. Each roof beam and a corresponding keel beam are positioned along a single butt line relative to an aircraft fuselage centerline. Frame members are coupled to both keel beams and both roof beams.
    Type: Application
    Filed: October 9, 2019
    Publication date: April 15, 2021
    Applicant: Bell Textron Inc.
    Inventors: Nicholas Ralph Carlson, William Anthony Amante, Timothy Brian Carr
  • ADDITIVE MANUFACTURE PROPROTOR BLADE
    Publication number: 20210101672
    Abstract: An exemplary proprotor blade assembly includes a structural skin extending spanwise from a root to a tip and along a chord from leading edge to a trailing edge and a structural core positioned inside of the structural skin, the structural skin comprising hex-shaped structures oriented normal to the structural skin.
    Type: Application
    Filed: October 2, 2019
    Publication date: April 8, 2021
    Applicant: Bell Textron Inc.
    Inventors: Christopher Edward FOSKEY, Andrew MARESH
  • SPAR FOR DUCTED-ROTOR AIRCRAFT
    Publication number: 20210101676
    Abstract: An annular spar for a ducted-rotor of an aircraft may be fabricated from composite material, such as carbon-fiber-reinforced plastic (CFRP). The spar may include an annular plate, a first circumferential flange that extends from an outer edge of the plate, and a second circumferential flange that extends from an inner edge of the plate. The first and second circumferential flanges may taper inwardly toward a center axis of the spar. The spar may be constructed of a plurality of layers of CFRP. One or more of the layers may be fabricated from a single ply of CFRP, and one or more other layers may be fabricated from a plurality of plies of CFRP. The spar may exhibit a coefficient of thermal expansion (CTE) that allows an associated tip gap to remain essentially constant throughout a range of operating temperatures.
    Type: Application
    Filed: October 5, 2019
    Publication date: April 8, 2021
    Applicant: Bell Textron Inc.
    Inventors: Karl Schroeder, William Anthony Amante, Joseph Richard Carpenter, JR., David G. Carlson
  • Devices and methods to verify main rotor swashplate positioning
    Patent number: 10967990
    Abstract: A device to verify main rotor swashplate positioning includes an inner surface of a first section and a gradient surface of a second section. The gradient surface of the second section may have a plurality of graduation indications. In one implementation, the inner surface of the first section at least partially defines a travel arc that is parallel to and concentric with the inner surface. In such an implementation, the device may be configured to move along the travel arc as it rotates about a collective sleeve to contact a swashplate lug.
    Type: Grant
    Filed: November 6, 2018
    Date of Patent: April 6, 2021
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Chad R. Haugeberg, Bradley D. Linton
  • Removable struts for vibration isolation device mounting system
    Patent number: 10967962
    Abstract: A strut assembly for a vibration isolation device is disclosed, comprising a piston spindle; a first elastomeric member and a second elastomeric member bonded to the piston spindle and in contact with an upper housing and a lower housing, respectively; a first strut support and a second strut support attached to or integral with the upper housing and the lower housing, respectively; a first strut spindle and the second strut support configured to be placed in the first strut support and the second strut support, respectively; and one or more removable struts configured to be engaged to the first strut spindle and to the second strut spindle, wherein at least one of the first or second strut spindles is removable such that the one or more struts can be replaced without breaking a bonding of the first elastomeric member, the second elastomeric member, or both.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: April 6, 2021
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Mark Wiinikka, Scott Hemmen, Nathan P. Green, James Blake
  • STOWED BLADE ACTIVE RESTRAINT
    Publication number: 20210094683
    Abstract: An exemplary clamp system for securing a proprotor blade in a stowed position includes a clamp having a pair of opposing pads operable between an open position to receive a portion of a proprotor blade between the pair of opposing pads and a closed position to grip the portion of the proprotor blade with the pair of opposing pads and a rotary actuator in connection with the clamp to operate the clamp between the open and the closed position.
    Type: Application
    Filed: September 27, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventor: Christopher Edward FOSKEY
  • One-Piece Mast, Planetary Plate, and Web Carrier
    Publication number: 20210094679
    Abstract: Embodiments are directed to a rotor mast for an aircraft comprising a shaft portion, a carrier portion having a plate and a web, and frame segments that separate the web from the plate at a fixed distance. The shaft portion, the plate, the web, and the frame segments are as single component. A plurality of first holes are formed in the plate, and a plurality of second holes are formed in the web. Pairs of the first and second holes are aligned. Posts are mounted between each pair of first and second holes. Pinion gears are mounted on the posts. Roller bearings are mounted between the posts and pinion gears. An open region of the web is configured to allow a sun gear to mesh with the pinion gears.
    Type: Application
    Filed: September 30, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Colton Gilliland, Tyson Henry, Russell Mueller
  • ADJUSTABLE LANDING GEAR ASSEMBLY FOR USE IN AIRCRAFT
    Publication number: 20210094675
    Abstract: A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.
    Type: Application
    Filed: October 1, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Mark Loring Isaac, Kent Edwards Donaldson
  • Light Communication Slip Ring
    Publication number: 20210094684
    Abstract: Embodiments are directed to a rotor system for an aircraft comprising a gearbox configured to receive torque from a drive train, a mast having a first end and a second end, wherein the first end is attached to the gearbox and the mast configured to rotate in response to the torque from the drive train, a rotor hub attached to the second end of the mast, a first light transceiver mounted adjacent to the first end of the mast, wherein the first light transceiver is does not rotate relative to the mast, and a second light transceiver mounted adjacent to the second end of the mast, wherein the second light transceiver rotates with the mast.
    Type: Application
    Filed: September 26, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Michael Raymond Hull, Daniel Duane Donley
  • ROTOR ASSEMBLY
    Publication number: 20210094674
    Abstract: A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.
    Type: Application
    Filed: October 1, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: George Matthew Thompson, Charles Hubert Speller, Jonathan Knoll
  • HUB WITH INTEGRAL ELASTOMERIC BEARING
    Publication number: 20210094680
    Abstract: A rotor hub assembly includes a yoke and a high capacity laminated (HCL) bearing, comprising layers of elastomeric material and layers of metal. The HCL bearing is affixed to the yoke to prevent separation of the HCL bearing from the yoke.
    Type: Application
    Filed: October 1, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Whitney Renee Foskey, Gary Miller
  • Multimode Powertrains for Multi Engine Rotorcraft
    Publication number: 20210094698
    Abstract: A powertrain for a rotorcraft includes first and second engines and a transmission system that includes a main rotor gearbox, a first freewheeling unit coupling the first engine to the main rotor gearbox and a second freewheeling unit coupling the second engine to the main rotor gearbox. The first freewheeling unit has a driving configuration and a bypass configuration. In a preflight configuration of the rotorcraft, the first engine provides power to at least one auxiliary component with the first freewheeling unit in the bypass configuration while the second engine provides power to the main rotor. In a flight configuration of the rotorcraft, the first engine provides power to the main rotor with the first freewheeling unit in the driving configuration while the second engine also provides power to the main rotor.
    Type: Application
    Filed: September 27, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Carlos Alexander Fenny, Gilberto Morales, Ryan Thomas Ehinger
  • Balance Weight Assemblies for Rotor Blades
    Publication number: 20210094677
    Abstract: A balance weight assembly for a rotor blade of a rotorcraft. The balance weight assembly includes a balance weight pocket formed by a balance weight tray and a cover. The balance weight tray has an upper surface including a lip region extending outwardly from a projected region with an outboard boss. A balance weight receiving cavity is recessed from the upper surface and contains a plurality of balance weights. The projected region is disposed within an opening in a hollow blade spar such that the outboard boss of the balance weight tray has a contact relationship with an outboard surface of the opening. The cover is coupled to the balance weight tray such that the lip region of the balance weight tray and at least a portion of the cover have a clamping relationship with the blade spar, thereby coupling the balance weight pocket to the blade spar.
    Type: Application
    Filed: September 30, 2019
    Publication date: April 1, 2021
    Applicant: Bell Textron Inc.
    Inventors: Tyler Wayne Baldwin, Jared Mark Paulson, Colin John Thomas, Paul Branson Sherrill, Bryan Huber