Patents Assigned to Textronics, Inc.
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Publication number: 20190016457Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket with an outboard surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a shear bearing and a centrifugal force bearing having an integral shoe with an outboard surface. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. The integral shoes are coupled to the yoke such that there is a spaced apart relationship between the outboard surfaces of the integral shoes and the outboard surfaces of the pockets to prevent centrifugal force load transfer therebetween.Type: ApplicationFiled: May 26, 2018Publication date: January 17, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Robert Patrick Wardlaw, John Richard McCullough, Amarjit Olenchery Kizhakkepat, Tyler Wayne Baldwin
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Patent number: 10179438Abstract: A method of manufacturing a door skin and a fuselage wall having a doorway and a member extending into the doorway for abutting the door includes placing a first sheet of uncured composite material on a mold plate to define the door and fuselage skin, disposing an insert over the first sheet overlapping a desired periphery of the door, placing a second sheet of uncured composite material on a peripheral portion of the insert and over the first sheet adjacent the peripheral portion of the insert to form the member, curing the sheets and bonding the sheets together adjacent the insert during the cure, removing the insert from between the sheets after cure, and separating the door skin from the wall skin after cure by moving a cutting tool through the first sheet and without penetrating the second sheet around the desired periphery of the door. An assembly for manufacturing the door skin and a fuselage wall is also discussed.Type: GrantFiled: September 23, 2016Date of Patent: January 15, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Sylvain Tessier, Richard Gingras, Jacques Dionne, Bryan Linington
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Publication number: 20190009898Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.Type: ApplicationFiled: July 10, 2017Publication date: January 10, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeffrey M. Bosworth, Kyle T. Cravener
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Patent number: 10173348Abstract: A method of manufacturing a self-supporting, monolithic fuselage body, including engaging peripheral mandrel sections around at least one central mandrel section, placing uncured composite material on the mold surface, curing the composite material on the mold surface, and sliding the central mandrel section(s) out of engagement with the peripheral mandrel sections and disengaging the peripheral mandrel sections from the cured composite material without collapsing the mandrel sections. The peripheral mandrel sections each include a shape-retaining core of a thermally insulating material and an outer layer on an outer surface of the shape-retaining core. The outer layer has a coefficient of thermal expansion within the range of variation of that of the coefficient of thermal expansion of the composite material. A mandrel for layup and cure of a predetermined composite material in the manufacture of a monolithic fuselage is also discussed.Type: GrantFiled: September 13, 2016Date of Patent: January 8, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Sylvain Tessier, Richard Gingras, Jacques Dionne, Felix Bednar
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Patent number: 10173787Abstract: A rotor speed indication system configured to communicate a rotor speed operating range for a twin engine rotorcraft having a rotor during one engine inoperable conditions. The rotor speed indication system includes a governing reference indicator located on a display and configured to communicate an upper operating range threshold. A droop reference indicator located on the display and configured to communicate a lower operating range threshold. A sensor configured to measure a current rotor speed of the rotor. A dynamic rotor speed indicator located on the display and configured to communicate the current rotor speed of the rotor such that when the dynamic rotor speed indicator is positioned between the governing reference indicator and the droop reference indicator on the display, the current rotor speed of the rotor is within the rotor speed operating range.Type: GrantFiled: February 12, 2018Date of Patent: January 8, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Erik John Oltheten, Aaron Thomas Halverson
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Patent number: 10173771Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.Type: GrantFiled: May 26, 2018Date of Patent: January 8, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Steven Ray Ivans, Nathan Gabriel Wu
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Patent number: 10173785Abstract: A combined controller with a panel that has a face and a back, a case attached to the back of the panel. The face of the panel includes a plurality of first primary flight display inputs configured to receive physical inputs for the control of a first primary flight display; a plurality of second primary flight display inputs configured to receive physical inputs for the control of a second primary flight display; and a plurality of flight control inputs configured to receive physical inputs for the control of automated flight behavior.Type: GrantFiled: June 8, 2017Date of Patent: January 8, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Joe Leachman, Thomas B. Priest
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Publication number: 20190002085Abstract: A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.Type: ApplicationFiled: June 28, 2017Publication date: January 3, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jouyoung Jason Choi, Thomas Clement Parham, JR., Gary Miller, Frank Bradley Stamps
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Publication number: 20190003944Abstract: A method for defining a threshold stress curve utilized in fatigue and/or damage tolerance analysis, the method including conducting a direct test method on a plurality of specimens with a notch to generate raw data, the notch in each of the specimens having a notch dimension; determining a plurality of analyzed data points based upon the raw data; determining a regression line based upon the plurality of data points, the regression line including an exponential portion and a power law portion; and connecting the exponential portion and the power law portion of the regression line to form a threshold stress curve based on the regression line.Type: ApplicationFiled: September 7, 2018Publication date: January 3, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Xiaoming Li, Bogdan R. Krasnowski
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Publication number: 20190003942Abstract: A bipendulum impact test machine for imparting impact damage includes a frame of beams where a weighted sled swings from a pair of links extending from a carriage. The carriage and sled are vertically adjustable along a set of vertical shafts of the frame. The sled is permanently horizontally oriented and parallel with the carriage. Interchangeable impact tips are removably and adjustably engaged with the sled. The impact tips have a variety of shapes in order to simulate different impact scenarios. The device is mobile and capable of imparting impact damage to large aircraft parts even in an installed condition.Type: ApplicationFiled: June 30, 2017Publication date: January 3, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Kevin Thomas HOWIE
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Publication number: 20190002112Abstract: A breakaway cover for providing emergency access to a release mechanism for a life raft on a vehicle includes a housing configured to be attached the vehicle. The housing includes a recess wherein the release mechanism may be located. The recess is protected by a cover. The cover has a first end attached the housing and a second end retained to the housing but capable of being pulled free. The cover is configured to fracture along a series of slots proximate the first end when pulled by a user.Type: ApplicationFiled: June 28, 2017Publication date: January 3, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Timothy Brian Carr, Chad Richard Haugeberg, Deepak Chandrashekar Jangamakote
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Publication number: 20190002078Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly.Type: ApplicationFiled: June 29, 2017Publication date: January 3, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Thomas Clement Parham, Jr., Jeffrey Bosworth, Gary Miller, Frank Bradley Stamps, Jouyoung Jason Choi, Paul K. Oldroyd, Richard Erler Rauber, Michael Scott Seifert
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Patent number: 10167080Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.Type: GrantFiled: September 19, 2016Date of Patent: January 1, 2019Assignee: Bell Helicopter Textron Inc.Inventor: Christopher Edward Foskey
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Publication number: 20180370621Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.Type: ApplicationFiled: August 3, 2018Publication date: December 27, 2018Applicant: Bell Helicopter Textron Inc.Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
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Publication number: 20180374287Abstract: Systems and methods are provided for statistically equivalent level of safety modeling. One method includes identifying sub-fleets within a fleet based upon usage profiles, determining a sub-fleet reliability value for each sub-fleet, determining a baseline fleet reliability for the fleet by combining the sub-fleet reliability values on a weighted basis, applying at least one credit to at least one sub-fleet, determining a post-credit sub-fleet reliability value for each sub-fleet based upon the at least one credit, determining a post-credit fleet reliability for the fleet by combining the post-credit sub-fleet reliability values on a weighted basis, comparing the baseline fleet reliability with the post-credit fleet reliability to identify a change in fleet reliability and determining whether the change in fleet reliability is within a predetermined threshold to validate the at least one credit.Type: ApplicationFiled: August 14, 2018Publication date: December 27, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Brian Edward Tucker, Richard Marcos Muñiz
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Publication number: 20180372793Abstract: A testing system and method are provided. A storage unit has stored therein a test procedure comprising one or more instructions for testing a system under test. A workstation is remotely interfaced with the system under test. The workstation comprises a test unit configured to retrieve the test procedure from the storage unit and to simulate at least one operation on the system under test in real-time for testing the system under test in accordance with the one or more instructions.Type: ApplicationFiled: July 30, 2017Publication date: December 27, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Sebastien Giroux, Cedric Roche
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Publication number: 20180372210Abstract: A pressure sensitive bypass valve for protecting the components of a fluid distribution system. The bypass valve includes a poppet designed to prevent fluid bypass in the event of spring failure, rather than from over-pressurization.Type: ApplicationFiled: June 26, 2017Publication date: December 27, 2018Applicant: Bell Helicopter Textron Inc.Inventor: Scott David Poster
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Patent number: 10160028Abstract: A flexible bladder can be expanded to insert a tool by implementing a tool assembly that includes an elongated hollow member including a hollow portion to receive at least one of a flexible bladder or a tool. An inlet member is attached to an end of the elongated hollow member. The inlet member receives at least one of the flexible bladder or the tool. A port is positioned on the elongated hollow member to apply vacuum inside the elongated hollow member.Type: GrantFiled: February 3, 2015Date of Patent: December 25, 2018Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Mark Mays, Brian S. Modrzejewski, Dan Brungs, Doug Wylin
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Patent number: 10160837Abstract: According to one embodiment, a method of dispersing nanoparticles into a destination material includes providing a plurality of nanoparticles suspended in a carrier, adding a solvent to the plurality of nanoparticles suspended in a carrier, removing at least some of the carrier to yield the plurality of nanoparticles suspended in the solvent, mixing the nanoparticles suspended in the solvent with a destination material, and removing at least some of the solvent from the mixture of nanoparticles suspended in the solvent and the destination material.Type: GrantFiled: December 19, 2017Date of Patent: December 25, 2018Assignee: Bell Helicopter Textron Inc.Inventors: Iosif Daniel Rosca, Martin Salameh, Suong Van Hoa
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Publication number: 20180362145Abstract: In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.Type: ApplicationFiled: December 15, 2017Publication date: December 20, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Christopher E. Foskey, Brendan P. Lanigan