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公开(公告)号：US12204321B2
公开(公告)日：2025-01-21
申请号：US17073214
申请日：2020-10-16
Applicant: Bell Textron Inc.
Inventor： Sébastien Lacasse , Ikram Djafri
Abstract: Methods and systems for performing a validation process on a part to be processed are provided. An identifier associated with the part is received. A listing of at least one automated process based on the identifier is displayed. An indication of a selected automated process from the listing is received. First instructions are transmitted to an automated process device for performing an automated processing program in accordance with the selected automated process. Processing results associated with the part are received from the automated process device. Second instructions are transmitted to a validation process device for performing a validation program in accordance with a validation process associated with the selected automated process. Validation results associated with the part are received from the validation process device. The processing results and the validation results are stored in association with the identifier.
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公开(公告)号：US12151811B2
公开(公告)日：2024-11-26
申请号：US16538979
申请日：2019-08-13
Applicant: Bell Textron, Inc.
Inventor： Daniel Bryan Robertson , Kirk Landon Groninga
Abstract: According to one implementation of the present disclosure, a rotorcraft includes a fuselage, an airframe, a main rotor, first and second wings, and a wing rotation system. The wing rotation system may be coupled to the first and the second wings and includes a first drive shaft, a second drive shaft, and a uniform actuator. The first drive shaft may be coupled to the first wing for rotation around a central wing axis, the second drive shaft may be coupled to the second wing for rotation around the central wing axis, and the uniform actuator may be coupled between the first drive shaft and the airframe. Also, the wing rotation system can be configured to actuate rotation of the first and the second wings from a first direction to a second direction.
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公开(公告)号：US20230211879A1
公开(公告)日：2023-07-06
申请号：US17569818
申请日：2022-01-06
Applicant: Bell Textron Inc.
Inventor： Steven R. Ivans , Brent C. Ross , Mathew Chapdelaine , Berlin B. Benfield
CPC classification number: B64C39/024 , B64C1/1415 , B64C29/0008 , B64C2201/024 , B64C2201/128
Abstract: A vertical takeoff and landing (VTOL) aircraft, including: a vehicle controller circuit programmed to operate the VTOL aircraft without an onboard human operator; a rotor system; an airframe; and an external cargo coupling to receive an external payload of at least approximately 300 pounds beneath the airframe.
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公开(公告)号：US20230211876A1
公开(公告)日：2023-07-06
申请号：US17569996
申请日：2022-01-06
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
CPC classification number: B64C27/12 , B64D31/12 , B64D31/10 , B64D45/04 , F02C9/42 , F05D2220/329 , F05D2270/093 , F05D2270/13
Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.
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公开(公告)号：US20230210253A1
公开(公告)日：2023-07-06
申请号：US17569152
申请日：2022-01-05
Applicant: Bell Textron Inc.
Inventor： Michael Ross Wilkinson , James Everett Kooiman , Clegg Benjamin Brian Smith , Jeffrey Matthew Williams , Tjepke Heeringa , David G. Carlson
CPC classification number: A47B5/00 , B64D11/00 , A47B2200/0066
Abstract: An aircraft includes a fuselage having a former therein and a work platform system. The work platform system includes a platform that is moveable between a stowed configuration and a deployed configuration. The work platform system also has a hinge pin received by the platform. A platform stop is carried by the former and configured to inhibit rotation of the platform about the hinge pin when the platform is in the deployed configuration. The hinge pin is carried by the former.
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Patent Agency Ranking
公开(公告)号：US11628928B2
公开(公告)日：2023-04-18
申请号：US17191075
申请日：2021-03-03
Applicant: Bell Textron Inc.
Inventor： Clifton L. Harrell , Christos Bais , Curtis R. Higgens , Thomas Earl Johnson, Jr. , David Adjei
Abstract: In an embodiment, a method of monitoring force equalization (FEQ) sensors on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a first measured force applied by a first actuation system in relation to a control surface, where the control surface is redundantly serviced by a plurality of actuation systems that include the first actuation system. The method also includes updating a measured-force time series for the first actuation system with the first measured force. The method also includes determining variation in at least a portion of the measured-force time series responsive to the updating. The method also includes identifying a first static condition in the measured-force time series in response to a determination that the variation in the measured-force time series is no greater than a minimum amount of variation.
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公开(公告)号：US11628923B2
公开(公告)日：2023-04-18
申请号：US16949868
申请日：2020-11-18
Applicant: Bell Textron Inc.
Inventor： Abey Kurikesu , Amarjit O. Kizhakkepat
Abstract: An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.
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公开(公告)号：US11628737B2
公开(公告)日：2023-04-18
申请号：US16780670
申请日：2020-02-03
Applicant: Bell Textron Inc.
Inventor： Michael Kevin McNair , Mark David Stoufflet
IPC: H02J7/00 , H02J7/14 , B60L53/62 , B64C39/02 , B64D41/00 , B60L53/36 , B60L53/66 , B60L53/50 , B60L58/12 , B60L53/14 , H01R13/642 , H01R13/62 , B60L53/12
Abstract: One embodiment includes an electrical tanker aircraft for in-flight recharging a worker aircraft, comprising: a charge source; an umbilical to engage an in-flight charge recipient aircraft; and control logic to determine that the umbilical has engaged the charge recipient aircraft, and to transfer charge until a termination condition is met.
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公开(公告)号：US11624604B2
公开(公告)日：2023-04-11
申请号：US16811088
申请日：2020-03-06
Applicant: Bell Textron Inc.
Inventor： Brennan Loyd Stults , Nicholas Anthony Stahl
Abstract: An example of a concentric probe includes an outer shroud having a bore that extends through the outer shroud, an inner shroud located within the outer shroud and having a bore that extends through the inner shroud, the inner shroud joined to the outer shroud via brazing, an annulus defined by a space between the inner shroud and a wall of the bore of the outer shroud, a plenum defined by a space between the inner shroud and the wall of the bore of the outer shroud, the plenum being in fluid communication with the annulus, and a transducer disposed within inner shroud.
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公开(公告)号：US20230067093A1
公开(公告)日：2023-03-02
申请号：US17410442
申请日：2021-08-24
Applicant: Bell Textron Inc.
Inventor： Andrew Maresh , Kyle Cravener
Abstract: Disclosed is a blade lock assembly, which may include a drag brace coupled to a fold crank assembly and to a rotary wing blade and may further include an actuator assembly configured to be coupled to a rotary wing cuff. The actuator assembly may include an actuator pin housing, an actuation pin at least partially sheathed by the actuator pin housing, and an actuator configured to extend and retract the actuation pin away from and toward the actuator pin housing.
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