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公开(公告)号：US10988243B2
公开(公告)日：2021-04-27
申请号：US16354421
申请日：2019-03-15
Applicant: Bell Textron Inc.
Inventor： Andrew Paul Haldeman , Gary Miller
Abstract: A tension-torsion strap, for example for a rotor aircraft, including a continuous length of carbon fiber tow arranged in multiple loops to form an elongated member extending between opposing ends and a flexible cover encasing the carbon fiber tow.
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公开(公告)号：US20210114715A1
公开(公告)日：2021-04-22
申请号：US16655400
申请日：2019-10-17
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas CRAVENER , Andrew MARESH , Chyausong TZENG
Abstract: An exemplary length adjustable link includes a tube having an internal bore and internal surface, a first rod end having a first shaft disposed in a first end of the internal bore, a second rod end having a second shaft disposed in a second end of the internal bore, and a member threadably connecting the first rod end to the second rod end.
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公开(公告)号：US20210107624A1
公开(公告)日：2021-04-15
申请号：US16599483
申请日：2019-10-11
Applicant: Bell Textron Inc.
Inventor： Kyle Thomas CRAVENER , Christopher Edward FOSKEY , Andrew MARESH
IPC: B64C11/28 , B64C29/00 , B64C27/80 , B64C27/605 , B64C27/64 , B64C27/59 , B64C11/32 , B64C27/57 , B64C11/38
Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.
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公开(公告)号：US20210096562A1
公开(公告)日：2021-04-01
申请号：US16585920
申请日：2019-09-27
Applicant: Bell Textron Inc.
Inventor： Paul David Ruckel , Jeremy Robert Chavez
Abstract: In an embodiment, a method includes: adjusting a first flight control device of a rotorcraft to control flight around a first axis of the rotorcraft, the first flight control device exercising flight control authority around the first axis of the rotorcraft; detecting a failure of the first flight control device; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to a second flight control device of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device; and adjusting the second flight control device to control flight around the first axis of the rotorcraft, the second flight control device being adjusted by a first control process when the rotorcraft is in a first flight mode, the second flight control device being adjusted by a second control process when the rotorcraft is in a second flight mode.
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公开(公告)号：US20210094698A1
公开(公告)日：2021-04-01
申请号：US16585891
申请日：2019-09-27
Applicant: Bell Textron Inc.
Inventor： Carlos Alexander Fenny , Gilberto Morales , Ryan Thomas Ehinger
IPC: B64D31/14 , B64D27/14 , B64C27/06 , B64D41/00 , B64D35/02 , B64D35/08 , F16D41/12 , F16D25/12 , F16D25/00
Abstract: A powertrain for a rotorcraft includes first and second engines and a transmission system that includes a main rotor gearbox, a first freewheeling unit coupling the first engine to the main rotor gearbox and a second freewheeling unit coupling the second engine to the main rotor gearbox. The first freewheeling unit has a driving configuration and a bypass configuration. In a preflight configuration of the rotorcraft, the first engine provides power to at least one auxiliary component with the first freewheeling unit in the bypass configuration while the second engine provides power to the main rotor. In a flight configuration of the rotorcraft, the first engine provides power to the main rotor with the first freewheeling unit in the driving configuration while the second engine also provides power to the main rotor.
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Patent Agency Ranking
公开(公告)号：US20210094676A1
公开(公告)日：2021-04-01
申请号：US16588097
申请日：2019-09-30
Applicant: Bell Textron Inc.
Inventor： Jeffrey BOSWORTH , Robert VELTRE
Abstract: An exemplary tiltrotor aircraft includes a fuselage carrying a wing, a pylon assembly coupled to the wing such that the pylon assembly is rotatable to selectively operate the tiltrotor aircraft between a helicopter mode and an airplane mode, a vibration isolator assembly connected to the pylon assembly and the wing including a first vibration isolator configured to isolate vibration in a vertical plane a second vibration isolator configured to isolate vibration in a lateral plane.
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公开(公告)号：US20210088409A1
公开(公告)日：2021-03-25
申请号：US16579446
申请日：2019-09-23
Applicant: Bell Textron, Inc.
Inventor： Steven R. Quick , Cyrus Elliott Rahimzadeh
IPC: G01M13/02
Abstract: A system and method for verifying a mechanical system chip detection capability, the method including determining a slurry injection location in machinery according to a targeted obstruction in the machinery in relation to a target chip detector of the machinery, placing an injection tube through a machinery casing of the machinery, providing a slurry tube connected to the injection tube, the slurry tube containing a slurry comprising conductive chips and a lubricant, operating the machinery until the machinery meets one or more predetermined operating parameters, injecting the slurry into the machinery casing during operation of the machinery and after the machinery meets the one or more predetermined operating parameters, and monitoring the target chip detector for detection of the conductive chips during the operation of the machinery.
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公开(公告)号：US20210078699A1
公开(公告)日：2021-03-18
申请号：US16575329
申请日：2019-09-18
Applicant: Bell Textron Inc.
Inventor： Paul Branson Sherrill , Robert Patrick Wardlaw , Robert Alan Self
IPC: B64C27/473 , B64C27/00 , F01D5/28 , B29D99/00
Abstract: In an implementation, a rotor blade for a helicopter may include an outer layer. The outer layer may have a leading edge region and a trailing edge region and may define a cavity. The leading edge region may include a first shape at least partially corresponding with an airfoil, e.g., a wing. An insert may be included within the cavity and be encompassed thereby. The insert may include a shape that substantially corresponds with the first shape, e.g., the insert may substantially correspond with a leading edge of an airfoil. The insert may have a plurality of weight shot each of which may be surrounded by a binding agent.
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公开(公告)号：US20210070433A1
公开(公告)日：2021-03-11
申请号：US16563732
申请日：2019-09-06
Applicant: Bell Textron Inc.
Inventor： Paul Branson Sherrill , Robert Alan Self
IPC: B64C27/473 , F01D5/14 , B64F5/10
Abstract: In an implementation, a rotor blade (alternatively referred to herein as “blade”) for a helicopter or other aircraft may include an outer layer. The outer layer may define a cavity. The outer layer may at least partially correspond to an airfoil, e.g., a wing. One or more inserts may be included within the cavity and be encompassed thereby. The first insert may have a density of at least 0.6 pounds per cubic inch.
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公开(公告)号：US20210070432A1
公开(公告)日：2021-03-11
申请号：US16561516
申请日：2019-09-05
Applicant: Bell Textron Inc.
Inventor： Andrew Ryan Maresh , Chyausong Tzeng , Russell Mueller
Abstract: Embodiments are directed to a double Hooke's joint gimbal in a rotor system. An upper Hooke's joint has four arms extending radially outward to define first and second axes, and a lower Hooke's joint has four arms extending radially outward to define third and fourth axes. A pair of connectors couple the upper Hooke's joint and the lower Hooke's joint. A first set of bearings are positioned between arms on the upper and lower Hooke's joints and the connectors. The first set of bearings comprise an elastomer, such as elastomeric journal bearings. The upper Hooke's joint is coupled to a yoke and rotor blades by a driver assembly that allows rotor blade flapping. The lower Hooke's joint is coupled to and driven by a mast. A spherical bearing allows the upper Hooke's joint to move laterally along the mast.
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