Patents Assigned to Textronics, Inc.
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Publication number: 20190276157Abstract: A radial inlet plenum a forward panel, an aft panel, and a cowling extending therebetween. The forward and aft panels are coupled between the cowling and an engine. The forward and aft panels include flexible sections to allow the engine to translate radially and axially, as well as rotate, relative to the cowling.Type: ApplicationFiled: March 8, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Marc Ouellet, Guillaume Noiseux-Boucher
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Publication number: 20190280427Abstract: A hinged strain relief backshell, selectively disposed about a cable, adjacent to a cable connector for selective assembly with the connector, includes a first integral semi-cylindrical backshell half and a second integral semi-cylindrical backshell half second hinged to the first integral backshell half. The integral semi-cylindrical backshell halves configured to be to be selectively disposed about the cable with one another. Each integral semi-cylindrical backshell half defining complementary half-threads defined by the respective backshell half and corresponding wrench flats defined in an outside surface portion of each backshell half. At least one of the integral semi-cylindrical backshell halves defining at least one strain clamp ear portion extending from a connector distal portion of the backshell half for retraining the cable at least in a direction parallel to the cable.Type: ApplicationFiled: March 6, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Patrick David Reibel, Jeremy William DeWaters, Matthew Ryan Carr
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Publication number: 20190276145Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.Type: ApplicationFiled: May 23, 2019Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventors: John Richard McCullough, Paul K. Oldroyd
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Publication number: 20190276142Abstract: A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine coupled to a freewheeling unit. A gear system positioned between the freewheeling unit and a proprotor assembly has a torque path coupling assembly disposed between an engine side gear assembly and a rotor side gear assembly. In a disengaged position, the torque path coupling assembly interrupts the torque path between the engine and the proprotor assembly. In an engaged position, the torque path coupling assembly completes the torque path between the engine and the proprotor assembly. A hybrid power unit is configured to accelerate the engine side gear assembly to match the output rotating speed to the input rotating speed enabling the torque path coupling assembly to shift from the disengaged position to the engaged position.Type: ApplicationFiled: December 6, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Mark Alan Przybyla
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Publication number: 20190276158Abstract: An active cooling system includes a sensor configured to monitor a status of a lubrication system of a lubricated component and a cowling configured to cover at least a portion of the lubricated component. The cowling includes an inlet panel configured to move from a normal operating position to a cooling position, wherein the cooling position creates an air inlet configured to increase airflow passing by the lubricated component. The active cooling system further includes an actuator configured to initiate movement of the inlet panel from the normal operating position to the cooling position.Type: ApplicationFiled: March 8, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric A. Sinusas, Ryan Thomas Ehinger
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Publication number: 20190277353Abstract: A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine that is coupled to a freewheeling unit. A gear system has a torque path coupling assembly between a first gear assembly that is coupled to the freewheeling unit and a second gear assembly that is coupled to a proprotor assembly. The torque path coupling assembly has an engaged position wherein the output of the first gear assembly is coupled to the input of the second gear assembly thereby providing a torque path between the engine and the proprotor assembly. The torque path coupling assembly also has a disengaged position wherein the output of the first gear assembly is independent of the input of the second gear assembly thereby interrupting the torque path between the engine and the proprotor assembly.Type: ApplicationFiled: March 7, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Mark Alan Przybyla
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Publication number: 20190279442Abstract: A failure detection system (FDS) for a gearbox has a power source disposed within the gearbox, a camera element disposed within the gearbox, a processor disposed within the gearbox.Type: ApplicationFiled: March 8, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Elizabeth Jasper
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Publication number: 20190277392Abstract: A cam-locking system for use with a retractable driveshaft that includes a housing, a cam carrier located at least partially the housing, and a cam rotatably coupled to the cam carrier. Translation of the cam carrier along a central axis allows the cam to rotate into cooperative engagement with a catch recess on an interior surface of the housing, preventing the cam carrier from translating backwards, and thereby maintaining the retractable driveshaft in an engaged position. Further advancement of the cam carrier allows that cam to rotate into and unlocking gap in the interior surface of the housing, which enables the cam carrier to translate backwards along the central axis below the locked position, thereby disengaging the retractable driveshaft.Type: ApplicationFiled: March 8, 2018Publication date: September 12, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Colton Gilliland
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Patent number: 10407157Abstract: An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.Type: GrantFiled: March 14, 2013Date of Patent: September 10, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Christopher Foskey, Frank B. Stamps, Richard Rauber
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Patent number: 10407154Abstract: In one embodiment, a horizontal stabilizer spar is held on the empennage of a rotorcraft by saddle fittings clamping the stabilizer spar at positions spaced apart along a longitudinal direction of the stabilizer spar. Stabilizer mounts are connected at respective ends to the saddle fittings and to vertical spars on the empennage. At least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom. The movable stabilizer mount is floatingly attached to a vertical spar, while the saddle fittings are connected to the respective stabilizer mounts by way of spherical bearings.Type: GrantFiled: April 18, 2017Date of Patent: September 10, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Guillaume Noiseux Boucher, Pascal Flynn-Robitaille, Kevin Donald Morris
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Patent number: 10408324Abstract: A hybrid composite and metallic gear includes a generally cylindrical shaft interface. A composite web is coupled to the shaft interface. The composite web includes a generally cylindrical rim having an outer surface. The outer surface includes a plurality of locks each having a radially outwardly extending profile. A generally cylindrical metallic gear ring having a plurality of external teeth includes an inner surface. The inner surface includes a plurality of detents each having a radially outwardly extending profile that corresponds with one of the locks of the composite web. When the composite web is positioned within the metallic gear ring, the corresponding locks and detents each form a lock and detent coupling establishing an interlocking interface between the composite web and the metallic gear ring.Type: GrantFiled: August 14, 2017Date of Patent: September 10, 2019Assignee: Bell Textron Inc.Inventors: Cody Clark Anderson, Gilbert Morales, Paul K. Oldroyd
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Patent number: 10406764Abstract: A method for repairing damage to a composite part includes creating an aperture through the composite part and preparing the surfaces surrounding the aperture on both sides of the part; inserting a plurality of resin impregnated fibers through the aperture and spreading the end portions of the plurality of fibers radially against the prepared surfaces on both sides of the part; and maintaining contact of the plurality of fibers with the prepared surfaces while the resin cures.Type: GrantFiled: August 30, 2017Date of Patent: September 10, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Denver Ray Whitworth, Vance Newton Cribb
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Patent number: 10407152Abstract: According to one embodiment, an aircraft features a fuselage, a wing member, and two fuselage beam. The fuselage features a first plurality of structural supports, a second plurality of structural supports, a first opening disposed between the first plurality of structural supports, and a second opening disposed between the second plurality of structural supports. The wing member is disposed above the first opening and above the second opening. The wing features a plurality of ribs including a first rib and a second rib. The first fuselage beam couples the first rib of the wing member to the fuselage and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam couples the second rib of the wing member to the fuselage and features an elongated body portion extending across the second plurality of structural supports.Type: GrantFiled: June 26, 2018Date of Patent: September 10, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: James Everett Kooiman, Mark Loring Isaac, John Elton Brunken, Jr., John McCullough
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Patent number: 10407160Abstract: In one embodiment, an apparatus may comprise a rotor blade. The rotor blade may comprise a plurality of blade segments; one or more attachment fittings for coupling the plurality of blade segments; and one or more actuators for adjusting an orientation of the plurality of blade segments.Type: GrantFiled: February 3, 2017Date of Patent: September 10, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventor: Benjamin A. Goldman
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Patent number: 10407169Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.Type: GrantFiled: August 30, 2016Date of Patent: September 10, 2019Assignee: Bell Textron Inc.Inventors: Kirk Landon Groninga, Daniel Bryan Robertson, Frank Bradley Stamps
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Patent number: 10408723Abstract: A method for determining a shear property of a sample includes supporting a sample at three or more separate support locations about a periphery of a first surface of the sample in a testing fixture, the sample including a second surface separated from the first surface by a thickness, wherein the sample is axisymmetric about an axis that is orthogonal to the first surface. The method includes applying a load on the second surface of the sample with a load applicator in a direction substantially parallel with the axis, measuring, with a controller, shear testing data of the sample in response to applying the load, and determining, with the controller, a shear property of the sample from the measured shear testing data.Type: GrantFiled: December 15, 2016Date of Patent: September 10, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Bogdan Roman Krasnowski, Xiaoming Li, Chyau Tzeng, Robert Patrick Wardlaw, Robert Arnold Brack
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Publication number: 20190270516Abstract: A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.Type: ApplicationFiled: March 1, 2018Publication date: September 5, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric A. Sinusas, Erik John Oltheten, Carlos Alexander Fenny
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Publication number: 20190271398Abstract: Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes an engine reduction gearbox having a retractable driveshaft that selectively engages the mid-wing gearbox via axially translatable motion along a rotation axis when the wing assembly is in the flight position. The mid-wing gearbox includes a plunger seal that is displaced in response to contact with the retractable driveshaft. Displacement of the plunger seal allows lubricant to flow through an inner bore in the retractable driveshaft, across splines of the retractable driveshaft and the mid-wing gearbox, and through lubrication ports in the mid-wing gearbox to lubricate the engine reduction gearbox, splines of the retractable driveshaft and the mid-wing gearbox, and the mid-wing gearbox via a single lubrication system.Type: ApplicationFiled: March 4, 2018Publication date: September 5, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric Stephen Olson, David Russell Bockmiller
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Patent number: 10400812Abstract: The present invention includes a method for fastening a fastener body having a longitudinal axis, a first external male threaded portion, and two or more through-holes perpendicular to the longitudinal axis of the fastener body in the first external male threaded portion, wherein the through-holes are on a different plane perpendicular to the longitudinal axis of the fastener, wherein the two or more through-holes are on a different one of the planes and angle from an adjacent through-hole of the two or more through-holes; and tightening a fastening member configured to matingly engage the first external male threaded portion, wherein the two or more through-holes is capable of receiving a pin without having to rotationally adjust the fastening member such that compression is maintained between a first object and a second object.Type: GrantFiled: March 20, 2017Date of Patent: September 3, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventor: Scott David Poster
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Patent number: 10399285Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the mold. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies.Type: GrantFiled: February 3, 2017Date of Patent: September 3, 2019Assignee: Bell Helicopter Textron Inc.Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, Andrew G. Baines, George R. Decker