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公开(公告)号:USD974277S1
公开(公告)日:2023-01-03
申请号:US29670415
申请日:2018-11-15
Applicant: Bell Helicopter Textron Inc.
Designer: Michael E. Rinehart
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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
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.
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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.
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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
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.
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公开(公告)号:US11255373B2
公开(公告)日:2022-02-22
申请号:US15702958
申请日:2017-09-13
Applicant: Bell Helicopter Textron Inc.
Inventor: Andrew Jordan Birkenheuer , Keith David Weaver , Jon Damon Bennett
Abstract: A thermal management system and method includes: a drive shaft; one or more fans or impellers in fluid communication with at least a portion of the drive shaft; and one or more air management baffles configured to direct air flow between the impeller and the portion of the drive shaft. In one embodiment, the system and method further includes insulation positioned about the at least a portion of the drive shaft.
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公开(公告)号:US11242158B2
公开(公告)日:2022-02-08
申请号:US16247745
申请日:2019-01-15
Applicant: Bell Helicopter Textron Inc.
Inventor: Christopher Edward Foskey , Chyau-Song Tzeng
Abstract: A rotor assembly for use in an aircraft comprising has a rotor hub, a spinner structure comprising a spinner opening, and a rotor blade received through the spinner opening. The rotor blade has a rotor root located proximate to the rotor hub. The rotor assembly also has a motive fairing face that at least partially rests along the rotor hub.
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公开(公告)号:US11220355B2
公开(公告)日:2022-01-11
申请号:US16204995
申请日:2018-11-29
Applicant: Bell Helicopter Textron Inc.
Inventor: Jeffrey P. Nissen , Edward Hohman , Robert J. Barry
Abstract: A field deployable infrared imaging (FDIR) system and method for inspecting a composite component comprises a hand-held long-wave IR camera to capture a thermal image of the composite component, wherein the camera has an adjustable temperature control that captures an image with a 10 degree working range, a frame capture rate of at least 1 second for a length of time of not less than 90 seconds; and a processor for post-processing the thermal image using a second order derivative algorithm wherein the post-processed thermal image shows the defect better than the captured infrared image, and detects the one or more defects in the composite component.
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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
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.
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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
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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公开(公告)号:US20210393999A1
公开(公告)日:2021-12-23
申请号:US17462414
申请日:2021-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor: Bob Thornton , Chyau Tzeng , Brian Mesing , Kevin Knott , Mark Wiinikka , Edith Richard , David Platz , Joshua Edler , Sarah Villanueva , Thomas Mast , Joseph Leachman , Daniel John Burns
Abstract: The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.
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