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公开(公告)号：US20090229694A1
公开(公告)日：2009-09-17
申请号：US12045924
申请日：2008-03-11
Applicant: Carlos A. Fenny , Marc W. Kinard , John Lauffer
Inventor： Carlos A. Fenny , Marc W. Kinard , John Lauffer
CPC classification number: H03C1/34 , B64C13/42 , F15B2211/20576 , F15B2211/31535 , F15B2211/324 , F15B2211/7054 , F15B2211/7055 , F15B2211/7056 , F15B2211/7107 , F15B2211/8757 , H03C7/00 , Y02T50/44 , Y10T137/86606
Abstract: A hydraulic actuator is configured to provide redundant boost control to an aircraft within approximately the same space required by a single hydraulic cylinder. The hydraulic actuator includes a housing and a piston assembly disposed within the housing. The piston assembly includes a ram, a first piston secured to the ram, and second and third pistons disposed on the ram such that the second and third pistons are translatable relative to the longitudinal axis of the ram. The pistons form two hydraulically separate actuator cylinders within the space required by a single cylinder which results in a reduction in the weight and size of the hydraulic actuator.
Abstract translation: 液压致动器被配置为在单个液压缸所需的大致相同的空间内为飞机提供冗余升压控制。 液压致动器包括壳体和设置在壳体内的活塞组件。 活塞组件包括柱塞，固定到冲头的第一活塞，以及设置在冲头上的第二和第三活塞，使得第二和第三活塞可相对于压头的纵向轴线平移。 活塞在单个气缸所需的空间内形成两个液压分离的致动器气缸，这导致液压致动器的重量和尺寸的减小。
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公开(公告)号：US12240189B2
公开(公告)日：2025-03-04
申请号：US15937009
申请日：2018-03-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Dean Dearman , Jared Mark Paulson , Paul K. Oldroyd , Paul Sherrill
Abstract: A method for forming composite components includes disposing composite laminate over a mandrel. The method further includes infusing the composite laminate with a resin. A gelation of the infused resin is caused by applying a first environmental condition to the composite laminate and mandrel. At least a portion of the mandrel is deformed by applying a second environmental condition to the composite laminate and mandrel. The method further includes forming a composite structure by curing the composite laminate infused with resin. The deformed mandrel is removed from the composite structure after forming the composite structure.
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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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公开(公告)号：US12202594B2
公开(公告)日：2025-01-21
申请号：US17165068
申请日：2021-02-02
Applicant: Bell Textron Inc.
Inventor： Eric Albert Sinusas , Edward Lambert , Yann Lavallee , Aaron Alexander Acee , Albert G. Brand
Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.
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公开(公告)号：US20250002142A1
公开(公告)日：2025-01-02
申请号：US18342123
申请日：2023-06-27
Applicant: Bell Textron Inc.
Inventor： Mark Loring Isaac
Abstract: An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.
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Patent Agency Ranking
公开(公告)号：US20250000017A1
公开(公告)日：2025-01-02
申请号：US18341830
申请日：2023-06-27
Applicant: Textron Inc.
Inventor： William Christopher Dickson
Abstract: One embodiment is a cutting assembly for a mower, the cutting assembly comprising a cutting unit comprising a plurality of blades; a lift arm including a float plate, wherein the cutting unit is connected to the lift arm via a yoke and wherein a slot is provided in the float plate; a lift actuator comprising a lift pin disposed in the slot; and a control system for selectively controlling a position of the lift actuator; wherein the position of the lift actuator comprises one of a first operating position, in which the lift pin is positioned proximate a center of the slot and a second operating position, in which the lift pin is positioned between the center of the slot and an end of the slot proximate a body of the actuator.
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公开(公告)号：US12174152B2
公开(公告)日：2024-12-24
申请号：US17112879
申请日：2020-12-04
Applicant: Bell Textron Inc.
Inventor： Corbin Tod Freitag
IPC: G01N3/08
Abstract: A test apparatus includes a first grip, a second grip movable relative to the first grip, a test specimen disposed to provide a load path between the first grip and the second grip, and a test chamber disposed to both substantially envelope the test specimen and move with one of the first grip and the second grip. The test chamber does not contact the test specimen. Another test apparatus includes, a first grip, a second grip movable relative to the first grip, a test specimen disposed to provide a load path between the first grip and the second grip, a first test chamber disposed to both substantially envelope the test specimen and move with one of the first grip and the second grip, and a second test chamber disposed to both substantially envelope both the test specimen and the first test chamber.
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公开(公告)号：US20240410535A1
公开(公告)日：2024-12-12
申请号：US18329719
申请日：2023-06-06
Applicant: TEXTRON, INC.
Abstract: A canopy for a vehicle, wherein the canopy comprises a body that is structured and operable to protect passengers of the vehicle from rain, water and sunlight, wherein the body comprises a photoluminescent material that is structured and operable to illuminate in the absence of light such that the body is structured and operable to self-illuminate without a connection to an electrical power source.
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公开(公告)号：US12136720B2
公开(公告)日：2024-11-05
申请号：US17172363
申请日：2021-02-10
Applicant: Bell Textron Inc.
Inventor： William A. Amante , Karl H. Schroeder , Jessica A. Revere
IPC: B64C1/06 , F28F3/12 , H01M10/613 , H01M10/625 , H01M10/6554 , H01M10/6556 , F28D21/00
Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.
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公开(公告)号：US12134481B2
公开(公告)日：2024-11-05
申请号：US17192478
申请日：2021-03-04
Applicant: Bell Textron Inc.
Inventor： Thuvaragan Senthilnathan , Chen Kuang
Abstract: Various implementations directed to an aircraft thermal management system are provided. In one implementation, an aircraft may include a fuselage having one or more fuselage sections. The aircraft may also include one or more electric motors configured to drive one or more propulsion systems of the aircraft, where the one or more electric motors are configured to generate thermal energy. The aircraft may further include an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections.
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