Patents Assigned to Textronics, Inc.
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Publication number: 20190185179Abstract: An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.Type: ApplicationFiled: December 19, 2017Publication date: June 20, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Cheng-Ho Tho, Michael Reaugh Smith
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Publication number: 20190185151Abstract: 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: ApplicationFiled: December 18, 2017Publication date: June 20, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jared Mark PAULSON, Tyler Wayne BALDWIN, Kyle Thomas CRAVENER
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Publication number: 20190185142Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.Type: ApplicationFiled: December 18, 2017Publication date: June 20, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jared Mark Paulson, Tyler Wayne Baldwin, Kyle Thomas Cravener
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Patent number: 10322797Abstract: A rotating sealing system includes a non-metallic rotating seal configured to be attached to a rotating shaft. The rotating seal is configured to rotate with the rotating shaft about an axis. The rotating sealing system includes a stationary sealing surface configured to be attached to a stationary housing positioned around the rotating shaft. The stationary sealing surface is substantially parallel to the axis. The rotating seal is configured to seal with the stationary sealing surface as the rotating shaft rotates.Type: GrantFiled: March 3, 2015Date of Patent: June 18, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Travis Jurrell, Timothy Cecil, Scott Poster, Wesley Porter
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Patent number: 10322799Abstract: In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.Type: GrantFiled: June 6, 2018Date of Patent: June 18, 2019Assignee: Bell Helicopter Textron Inc.Inventors: John Richard McCullough, Paul K. Oldroyd
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Publication number: 20190176980Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.Type: ApplicationFiled: December 7, 2017Publication date: June 13, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Albert G. Brand, Mark Loring Isaac, Frank Bradley Stamps, Russell Lee Mueller
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Publication number: 20190176976Abstract: A landing gear system for an aircraft includes an aft landing gear fitting coupled to the aircraft and a cross tube rotatably coupled to the aft landing gear fitting. The landing gear system also includes first and second wheel fittings coupled to the first and second ends of the cross tube, respectively, and first and second wheels rotatably coupled to the first and second wheel fittings, respectively.Type: ApplicationFiled: December 13, 2017Publication date: June 13, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sebastien Duval, Marc Ouellet
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Patent number: 10315779Abstract: In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.Type: GrantFiled: September 19, 2017Date of Patent: June 11, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Christopher M. Bothwell, Robert Earl Worsham, II, Sung Kyun Kim, Brandon Jeffrey Thomas
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Patent number: 10315761Abstract: In some embodiments, a propulsion assembly for an aircraft includes a nacelle, at least one self-contained fuel tank disposed within the nacelle operable to contain a liquid fuel, an engine disposed within the nacelle operable to run on the liquid fuel, a drive system mechanically coupled to the engine and operable to rotate responsive to rotation of the engine, a rotor hub mechanically coupled to the drive system operable to rotate responsive to rotation of the drive system and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith.Type: GrantFiled: July 1, 2016Date of Patent: June 11, 2019Assignee: Bell Helicopter Textron Inc.Inventors: John Richard McCullough, Paul K. Oldroyd
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Patent number: 10317323Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.Type: GrantFiled: October 12, 2017Date of Patent: June 11, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Ramesh Thiagarajan, Suvankar Mishra
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Publication number: 20190168879Abstract: A modal restraint system for an occupant of a seat of an aircraft includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant so as to dispose the occupant between the strap and the seat. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch to the fixed mode in response to a precautionary event, thereby reducing freedom of movement of the occupant relative to the seat of the aircraft.Type: ApplicationFiled: December 5, 2017Publication date: June 6, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric A. Sinusas, Olivier Andre Boisvert, Guillaume Noiseux-Boucher, Steve Loveland, Sebastien Duval
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Publication number: 20190168878Abstract: A modal restraint system for an occupant of a seat of an aircraft includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant so as to dispose the occupant between the strap and the seat. The strap feeder unit is adapted to switch between a plurality of modes including a fixed mode and an unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap feeder unit is in the fixed mode by default. The strap feeder unit is operable to switch to the unfixed mode in response to a user input, thereby increasing freedom of movement of the occupant relative to the seat of the aircraft.Type: ApplicationFiled: December 5, 2017Publication date: June 6, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric A. Sinusas, Olivier Andre Boisvert, Guillaume Noiseux-Boucher, Steve Loveland, Sebastien Duval
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Patent number: 10308356Abstract: A rotor hub assembly for a rotorcraft includes a yoke forming a bearing bore. The yoke has a teetering axis extending through the bearing bore. The rotor hub assembly includes a flapping bearing disposed in the bearing bore. The flapping bearing is operable to regulate teetering of the yoke about the teetering axis. The rotor hub assembly includes an axial spring abutting the flapping, thereby reducing movement of the flapping bearing along the teetering axis.Type: GrantFiled: November 22, 2016Date of Patent: June 4, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Dalton T Hampton, Thomas Clement Parham, Jr.
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Patent number: 10301032Abstract: An aircraft fuel system includes one or more fuel cells adapted to contain fuel, a fuel cell receiving assembly having an inner surface adapted to receive the one or more fuel cells and a fuel cell cushion disposed between the inner surface of the fuel cell receiving assembly and the one or more fuel cells. The fuel cell cushion is machined from a foam substrate to form a shaped foam substrate that is substantially covered with a cushion coating. The cushion coating is sprayable onto the shaped foam substrate such that the fuel cell cushion is substantially nonabsorbent of fuel. The fuel cell cushion is interposable between the inner surface of the fuel cell receiving assembly and the one or more fuel cells to cushion the one or more fuel cells from damage.Type: GrantFiled: February 27, 2017Date of Patent: May 28, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Timothy Brian Carr, Suvankar Mishra, Michael Stephen Deslatte, Michael Douglas Ishmael, Ronald James Turner
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Patent number: 10301010Abstract: An oscillating pump system includes a pump operable to circulate a fluid. The pump has a first port stage including an inlet port and an outlet port and a second port stage including a first oscillating port and a second oscillating port. An oscillator disk is disposed between the first port stage and the second port stage. The oscillator disk is rotatable relative to the inlet port, the outlet port, the first oscillating port and the second oscillating port. During rotation, the oscillator disk alternatingly routes the fluid to the inlet port from the first and second oscillating ports and alternatingly routes the fluid from the outlet port to the first and second oscillating ports, thereby generating oscillating fluid flow.Type: GrantFiled: October 20, 2016Date of Patent: May 28, 2019Assignee: Bell Helicopter Textron Inc.Inventor: David E. Heverly, II
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Publication number: 20190154137Abstract: According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.Type: ApplicationFiled: November 6, 2018Publication date: May 23, 2019Applicant: Bell Helicopter Textron Inc.Inventor: Ryan T. Ehinger
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Publication number: 20190152591Abstract: A braking system for a rotorcraft having a rotor hub assembly includes a generator having an armature mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly and a braking unit in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.Type: ApplicationFiled: January 24, 2019Publication date: May 23, 2019Applicant: Bell Helicopter Textron Inc.Inventor: John Robert Wittmaak
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Patent number: 10293931Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.Type: GrantFiled: August 31, 2016Date of Patent: May 21, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Daniel Bryan Robertson, Kirk Landon Groninga
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Publication number: 20190144126Abstract: A stacked motor assembly for an aircraft includes a forward motor having an exhaust port and an aft motor disposed aft of the forward motor, the aft motor having an intake port. The stacked motor assembly includes an exhaust conduit originating from the exhaust port of the forward motor and disposed at least partially around the aft motor such that exhaust from the forward motor bypasses the aft motor. The stacked motor assembly also includes an intake conduit terminating at the intake port of the aft motor and disposed at least partially around the forward motor such that intake air for the aft motor bypasses the forward motor.Type: ApplicationFiled: November 16, 2017Publication date: May 16, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Kirk Landon Groninga, Daniel Bryan Robertson
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Patent number: D848754Type: GrantFiled: June 27, 2018Date of Patent: May 21, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Andrew Zahasky, Levi Bilbrey