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公开(公告)号：US20200216170A1
公开(公告)日：2020-07-09
申请号：US16733806
申请日：2020-01-03
Applicant: Bell Textron Inc.
Inventor： Steven Loveland , Paul Charles Griffiths , Allen Brittain
Abstract: An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.
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公开(公告)号：US20200216164A1
公开(公告)日：2020-07-09
申请号：US16733798
申请日：2020-01-03
Applicant: Bell Textron Inc.
Inventor： James Gibson , Carey Cannon
IPC: B64C13/04
Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.
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公开(公告)号：US10697795B2
公开(公告)日：2020-06-30
申请号：US15894871
申请日：2018-02-12
Applicant: Bell Textron Inc.
Inventor： Erik John Oltheten , Aaron Thomas Halverson
Abstract: A navigation system for vehicles, such as rotorcraft, includes a directional gyroscope having a magnetic heading correction mode, a nonmagnetic manual heading correction mode and a nonmagnetic automatic heading correction mode. A magnetic field sensor is operably coupled to the directional gyroscope and is operable to generate magnetic north-based signals. A heading correction input is operably coupled to the directional gyroscope and is operable to generate manual signals upon actuation thereof. A global positioning system sensor is operably coupled to the directional gyroscope and is operable to generate track-based signals. In the magnetic heading correction mode, the directional gyroscope receives the magnetic north-based signals for heading corrections. In the nonmagnetic manual heading correction mode, the directional gyroscope receives the manual signals for heading corrections. In the nonmagnetic automatic heading correction mode, the directional gyroscope periodically receives the track-based signals for heading corrections.
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公开(公告)号：US10472059B2
公开(公告)日：2019-11-12
申请号：US15648650
申请日：2017-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Kyle Thomas Cravener , Amarjit Kizhakkepat , Ken Shundo , Jared Mark Paulson , Tyler Wayne Baldwin
Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.
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公开(公告)号：US10457380B2
公开(公告)日：2019-10-29
申请号：US15636448
申请日：2017-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Thomas Clement Parham, Jr. , Gary Miller , Frank Bradley Stamps
IPC: B64C11/06 , B64C27/35 , B64C27/51 , B64C27/635 , B64C29/00 , B64C11/32 , F16F15/121 , F16C23/04 , F16C27/02 , F16F15/12 , F16F15/124
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US10450054B2
公开(公告)日：2019-10-22
申请号：US15601658
申请日：2017-05-22
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , George Ryan Decker , Keith Alan Stanney , Robert Mark Chris
Abstract: An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.
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公开(公告)号：US10421540B1
公开(公告)日：2019-09-24
申请号：US15447966
申请日：2017-03-02
Applicant: Bell Helicopter Textron Inc.
Abstract: A tiltrotor aircraft is operable in a helicopter flight mode and an airplane flight mode. The tiltrotor aircraft has an airframe including a fuselage and a wing. First and second pylon assemblies are respectively coupled to the airframe proximate outboard ends of the wing. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. The pylon assemblies are rotatable relative to the wing to selectively operate the tiltrotor aircraft between the helicopter flight mode and the airplane flight mode. The thrust of each proprotor assembly has a thrust vector with an inboard angle between about 5 degrees and about 12 degrees relative to an axis parallel to the yaw axis during hover operations, thereby reducing download on the airframe and improving hover efficiency.
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公开(公告)号：US10407169B2
公开(公告)日：2019-09-10
申请号：US15251110
申请日：2016-08-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Kirk Landon Groninga , Daniel Bryan Robertson , Frank Bradley Stamps
Abstract: 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.
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公开(公告)号：US10392109B2
公开(公告)日：2019-08-27
申请号：US15341887
申请日：2016-11-02
Applicant: Bell Helicopter Textron Inc.
Abstract: An aircraft system includes a wing member and a plurality of unmanned aircraft systems selectively connectable to the wing member. The wing member has a generally airfoil cross-section, a leading edge and a trailing edge. The unmanned aircraft systems have a connected flight mode while coupled to the wing member and an independent flight mode when detached from the wing member. In the connected flight mode, the unmanned aircraft systems are operable to provide propulsion to the wing member to enable flight. The unmanned aircraft systems are operable to be launched from the wing member to perform aerial missions in the independent flight mode and are operable to be recovered by the wing member and returned to the connected flight mode. Thereafter, in the connected flight mode, the unmanned aircraft systems are operable to be resupplied by the wing member.
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公开(公告)号：US12237515B2
公开(公告)日：2025-02-25
申请号：US17508652
申请日：2021-10-22
Applicant: Bell Textron Inc.
Inventor： Phalgun Madhusudan
IPC: H01M4/86 , H01M4/88 , H01M4/92 , H01M8/0232 , H01M8/0245 , H01M8/0258 , H01M8/10 , H01M8/1004
Abstract: In certain embodiments, an apparatus includes an electrolyte membrane layer (EML), and includes a first electrode catalyst layer (ECL) and a first metallic gas diffusion layer (MGDL) positioned to a first side of the EML such that the first ECL is positioned between the first MGDL and the EML. The first MGDL includes a metal-containing layer and a coating of porous material disposed on a surface of the metal-containing layer of the first MGDL that faces the first ECL. The apparatus further includes a second ECL and a second MGDL positioned to the second side of the EML such that the second ECL is positioned between the second MGDL and the EML. The second MGDL includes a metal-containing layer and a coating of porous material disposed on a surface of the metal-containing layer of the second MGDL that faces the second ECL.
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