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    Rotorcraft anti-torque systems and methods therefor
    12.
    发明授权
    Rotorcraft anti-torque systems and methods therefor 有权

    公开(公告)号：US11433997B2

    公开(公告)日：2022-09-06

    申请号：US16399015

    申请日：2019-04-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Aaron A. Acee ,  Albert G. Brand ,  Frank B. Stamps

    IPC: B64C27/82 ,  B64C13/50 ,  B64C13/04

    Abstract: A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force.

    Rotor blade control system
    13.
    发明授权
    Rotor blade control system 有权

    公开(公告)号：US11427315B2

    公开(公告)日：2022-08-30

    申请号：US16453700

    申请日：2019-06-26

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Robert P. Reynolds ,  Glenn A. Shimek ,  Brady G. Atkins ,  William D. Girard

    IPC: B64C27/605 ,  B64C29/00

    Abstract: A rotor blade control system and methods therefor including a hub assembly pivotally attached to a rotor blade; a mast attached to the hub assembly; a swashplate assembly engaged with the mast and including a swashplate actuation mechanism pivotally coupled with the non-rotating ring at a plurality of coupling locations for moving the non-rotating ring and pivotally coupled with the base at a plurality of base locations, the swashplate actuation mechanism comprises a plurality of substantially triangular dual actuator assemblies that are independently and concurrently operable to move the respective coupling location so as to impart movement on the non-rotating ring. The swashplate actuation mechanism is configured to move the swashplate assembly about a longitudinal axis and a lateral axis in response to a cyclic input. The swashplate actuation mechanism is configured to move the swashplate assembly along the mast in response to a collective input.

    Tiltrotor with inboard engines
    14.
    发明授权
    Tiltrotor with inboard engines 有权

    公开(公告)号：US11370535B2

    公开(公告)日：2022-06-28

    申请号：US16196247

    申请日：2018-11-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Brent C. Ross ,  Steven R. Ivans

    IPC: B64C29/00 ,  B64D35/08 ,  B64C3/18 ,  B64D27/12

    Abstract: An aircraft is described and includes a fuselage, a wing coupled to the fuselage, and a rotor system including a proprotor system and an engine. An interconnect driveshaft gear is configured to communicate mechanical energy between a gearbox and an interconnect driveshaft. An accessory gear is coplanar with and in mechanical communication with the driveshaft gear. A proprotor gear is coplanar with and in mechanical communication with the interconnect driveshaft gear and the accessory gear and communicates mechanical energy to the proprotor system. An engine gear coplanar and in mechanical communication with the interconnect driveshaft ear, the accessory gear, and the proprotor gear transmits mechanical energy to the proprotor system via the proprotor gear.

    Bypass block for unregulated gearboxes
    18.
    发明授权
    Bypass block for unregulated gearboxes 有权

    公开(公告)号：US11209079B2

    公开(公告)日：2021-12-28

    申请号：US15967884

    申请日：2018-05-01

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Scott David Poster

    IPC: F16H57/04 ,  B64C27/12

    Abstract: The present invention includes a bypass apparatus for lubricant in an unregulated pressurized gearbox including: a block including a lubricant inlet in fluid communication with a pressure relief valve, wherein the pressure relief valve diverts lubricant into the gearbox or into an oil filter, wherein lubricant is returned to the gearbox when the lubricant is cold and/or pressure at the pressure relief valve is high to reduce damage to the gearbox caused by high pressure during a cold start, and when the lubricant temperature increases and the pressure is reduced the pressure relief valve closes and lubricant enters the oil filter.

    Rotorcraft elastomeric bearing assembly
    19.
    发明授权
    Rotorcraft elastomeric bearing assembly 有权

    公开(公告)号：US11208204B2

    公开(公告)日：2021-12-28

    申请号：US15815482

    申请日：2017-11-16

    Applicant: Bell Helicopter Textron Inc.

    Inventor： Christopher E. Foskey ,  Michael J. Southerland

    IPC: B64C27/35 ,  B64C11/04 ,  B64C29/00 ,  B64C27/00 ,  F16F1/38

    Abstract: In some embodiments, a rotorcraft may include a yoke, a blade, a spindle associated with the yoke, and an elastomeric bearing assembly. The center length of the spindle may define a center axis that passes through a center of the elastomeric bearing assembly. The elastomeric bearing assembly may contain a housing coupled to the blade and disposed around the center axis that is configured to rotate in relation to the center axis. The elastomeric bearing assembly may contain an elastomeric shear bearing that has an interior portion coupled to the spindle and an exterior portion coupled to the housing. The elastomeric bearing assembly may contain an elastomeric centrifugal force bearing pressed against the housing. The shear bearing may be configured to counteract a torsional force, and the centrifugal force bearing may be configured to counteract a compression force.

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