-
公开(公告)号：US20220281588A1
公开(公告)日：2022-09-08
申请号：US17191040
申请日：2021-03-03
Applicant: Bell Textron Inc.
Inventor： Clifton HARRELL , Christos BAIS , Curtis R. HIGGENS , Thomas Earl JOHNSON, JR. , David ADJEI
Abstract: In an embodiment, a method of managing force equalization (FEQ) on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a 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. The method also includes updating a measured-force time series for the first actuation system with the measured force. The method also includes analyzing movement over at least a portion of the measured-force time series. The method also includes identifying a force-fight cycle in the measured-force time series. The method also includes indicating the force-fight cycle in cumulative force-fight cycle data for the first actuation system.
-
公开(公告)号：US11420762B2
公开(公告)日：2022-08-23
申请号：US16679000
申请日：2019-11-08
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Paul Sherrill , Jonathan Knoll
Abstract: A rotor assembly including a rotor mast, a rotor hub coupled to the rotor mast, a plurality of rotor blades coupled to the rotor hub, a control tube extending through the rotor mast, a crosshead coupled to the control tube, and a mechanism configured to drive the rotor mast in rotation. Wherein the mechanism is longitudinally positioned between a top portion and a bottom portion of the control tube and translation of the control tube relative to the rotor mast causes rotation of the rotor blades about their pitch-change axes. While the crosshead is installed, the crosshead is prevented from angular rotation about the mast axis. A pin of a rotor blade assembly is captured between opposing tabs of the crosshead and movable relative to the opposing tabs in response to translation of the crosshead along the mast axis.
-
公开(公告)号：US20220258873A1
公开(公告)日：2022-08-18
申请号：US17175297
申请日：2021-02-12
Applicant: Bell Textron Inc.
Inventor： Guy Bernard , Jeffrey Epp , William K. Heironimus
Abstract: A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.
-
公开(公告)号：US11414184B2
公开(公告)日：2022-08-16
申请号：US16354591
申请日：2019-03-15
Applicant: Bell Textron Inc.
Inventor： Aaron Alexander Acee , Andrew Paul Haldeman , Eric Albert Sinusas , Yann Lavallee , Albert G. Brand
Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.
-
公开(公告)号：US20220221878A1
公开(公告)日：2022-07-14
申请号：US17149445
申请日：2021-01-14
Applicant: Bell Textron Inc.
Inventor： Steven G. Hagerott , Jonathan Andrew Toth
Abstract: There is disclosed in one example an inner loop controller for an aircraft flight computer, including: a stall protection circuit to compute, for an attitude angle θ, an attitude limit θmax as a function of a flight path angle (γ) and an angle of attack limit (αmax); a transfer function circuit to convert θ to an attitude rate {dot over (θ)}, wherein {dot over (θ)} is a time derivative of θ; and a load protector circuit to compute a limit on {dot over (θ)} ({dot over (θ)}max) as a function of a load factor limit (Nz,max) and a true airspeed (v).
-
Patent Agency Ranking
公开(公告)号：US20220219826A1
公开(公告)日：2022-07-14
申请号：US17148273
申请日：2021-01-13
Applicant: Bell Textron Inc.
Inventor： Jonathan Andrew Knoll , George Matthew Thompson , Charles Hubert Speller , Grant Michael Beall
Abstract: A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.
-
公开(公告)号：US20220204154A1
公开(公告)日：2022-06-30
申请号：US17139049
申请日：2020-12-31
Applicant: Bell Textron Inc.
Inventor： Robert W. Roe , Mark L. Isaac
Abstract: A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.
-
公开(公告)号：US20220204152A1
公开(公告)日：2022-06-30
申请号：US17135232
申请日：2020-12-28
Applicant: Bell Textron Inc.
Inventor： Kip Gregory Campbell
Abstract: One embodiment is an aircraft including a main body, a plurality of propulsion assemblies, and a plurality of hinges, wherein each of the plurality of propulsion assemblies is rotatably coupled to the main body using a hinge from the plurality of hinges. In an example, the aircraft includes four motor support arms and each motor support arm rotatably couples a specific propulsion assembly to a specific corresponding hinge on the main body of the aircraft and increases a span of the aircraft when the aircraft is in the flight configuration and reduces the footprint of the aircraft when the aircraft is in a storage configuration.
-
公开(公告)号：US20220187223A1
公开(公告)日：2022-06-16
申请号：US17118265
申请日：2020-12-10
Applicant: Bell Textron Inc.
Inventor： Steve CATES , Caydn WHITE , Kevin BROOKER
IPC: G01N23/207 , B64C27/00 , B64F5/60
Abstract: A method of evaluating fatigue damage of a rotor mast. The method includes performing an x-ray diffraction (“XRD”) inspection of the rotor mast, assessing fatigue damage sustained by the rotor mast based on results of the XRD inspection, and determining whether the rotor mast is suitable for continued use based on the assessed fatigue damage.
-
公开(公告)号：US20220177121A1
公开(公告)日：2022-06-09
申请号：US17116726
申请日：2020-12-09
Applicant: Bell Textron Inc.
Inventor： Alexander Dang Quang Truong , Karl Schroeder , Michael John Ryan
Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.
-
-
-
-
-
-
-
-
-
Search Results
685
records
(took 0.02 seconds)
