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    Modal tailboom flight control systems for compound helicopters
    4.
    发明授权
    Modal tailboom flight control systems for compound helicopters 有权

    公开(公告)号：US10933990B2

    公开(公告)日：2021-03-02

    申请号：US16247817

    申请日：2019-01-15

    Applicant: Bell Textron Inc.

    Inventor： Steven Ray Ivans

    IPC: B64C27/82 ,  B64C27/26

    Abstract: A modal tailboom flight control system for a compound helicopter is operable in a plurality of modes including a forward thrust mode and an anti-torque mode. The modal tailboom flight control system includes a tailboom, a drivetrain extending through the tailboom, an anti-torque system coupled to the drivetrain and rotatable to generate anti-torque thrust for the compound helicopter in the anti-torque mode and a pusher propeller coupled to the drivetrain and rotatable to generate forward thrust for the compound helicopter in the forward thrust mode. The pusher propeller is positioned forward of the anti-torque system.

    Convertible Biplane Aircraft for Capturing Drones
    5.
    发明申请
    Convertible Biplane Aircraft for Capturing Drones 审中-公开

    公开(公告)号：US20200290737A1

    公开(公告)日：2020-09-17

    申请号：US16743203

    申请日：2020-01-15

    Applicant: Bell Textron Inc.

    Inventor： Steven Ray Ivans ,  Jason Paul Hurst ,  Brent Chadwick Ross ,  John Richard McCullough ,  Paul K. Oldroyd

    IPC: B64C29/02 ,  G05D1/00 ,  B64C39/02 ,  B64D1/08 ,  B64C39/06 ,  B64D25/12

    Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

    Centerline tiltrotor
    6.
    发明授权
    Centerline tiltrotor 有权

    公开(公告)号：US11225323B2

    公开(公告)日：2022-01-18

    申请号：US16541561

    申请日：2019-08-15

    Applicant: Bell Textron Inc.

    Inventor： Keith Alan Stanney ,  Steven Ray Ivans ,  Brent Chadwick Ross ,  Troy Bushmire

    IPC: B64C27/28 ,  B64C17/02 ,  B64C3/56 ,  B64C27/50 ,  B64C27/26 ,  B64C27/82 ,  B64C1/30

    Abstract: Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

    TAIL SITTER STOP-FOLD AIRCRAFT
    7.
    发明申请
    TAIL SITTER STOP-FOLD AIRCRAFT 有权

    公开(公告)号：US20210253239A1

    公开(公告)日：2021-08-19

    申请号：US16795426

    申请日：2020-02-19

    Applicant: Bell Textron Inc.

    Inventor： Steven Ray Ivans ,  Brent Chadwick Ross ,  Danielle Lynn Moore ,  Berlin Bernard Benfield ,  Jason Paul Hurst

    IPC: B64C29/04 ,  B64C27/50 ,  B64D27/10 ,  B64D35/04 ,  B64C25/32 ,  B64C5/06 ,  B64C5/08 ,  B64C5/04 ,  B64C7/00

    Abstract: Embodiments are directed to a high speed, vertical lift aircraft that has vertical take-off and landing (VTOL) capability and is capable of converting to a forward-flight mode (e.g., prop-mode). The rotors blades can be folded for high speed forward flight propelled by a turbine engine (e.g., jet-mode). The rotor blades on the tail sitter aircraft have a “stop-fold” capability, which means that the rotor blades are stopped in flight and folded back to reduce drag. This allows the tail sitter aircraft to achieve a higher speed than a tilt-rotor aircraft. In some embodiments, the tail sitter aircraft achieves both rotor-borne flight and jet-borne flight by having two separate engines. An additional advantage of the tail-sitter aircraft versus a horizontally oriented fixed engine aircraft is that supplemental jet thrust can be used for take-off if desired.

    Centerline Tiltrotor
    9.
    发明申请
    Centerline Tiltrotor 有权

    公开(公告)号：US20210047029A1

    公开(公告)日：2021-02-18

    申请号：US16541561

    申请日：2019-08-15

    Applicant: Bell Textron Inc.

    Inventor： Keith Alan Stanney ,  Steven Ray Ivans ,  Brent Chadwick Ross ,  Troy Bushmire

    IPC: B64C27/28 ,  B64C29/02

    Abstract: Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

    Compound Helicopters having Hybrid Propulsion Engines
    10.
    发明申请
    Compound Helicopters having Hybrid Propulsion Engines 审中-公开

    公开(公告)号：US20200309066A1

    公开(公告)日：2020-10-01

    申请号：US16365573

    申请日：2019-03-26

    Applicant: Bell Textron Inc.

    Inventor： Brent Chadwick Ross ,  Steven Ray Ivans ,  Alan Carl Ewing

    IPC: F02K3/06 ,  B64C27/26 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F02C3/06

    Abstract: A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.

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